6 DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page : 1 of 

Printed in FRANCE © AIRBUS, 2007 All rights reserved

ATA SYSTEM : 28

TITLE : FUEL - TANKS - INSTALL TWO ACT PROVISIONS WITH CLS CONFIG

MODIFICATION No. : 25415P4179 25696P4347 25713J1492 25713K4481 26

26110K4482 26138K4772 27446P5502 27447P5503 274

27717K5539 28068P5759 28661J2073 28817J1973 30

30356P7357 30373K6720 31110K7004 31143K7155 31

31812K7403 32261J2241 33198K8488 33199K8489 33

33492J2482 34742K9642 34758K9658 36348K10556 3

36350K10558 36399K6099

This page transmits Revision No. 01 of Service Bulletin No. A320-

ADDITIONAL WORK

No additional work is required by this revision for aircraft m

previous issue.

REASON

Revision No. 01 is issued to add improvements following Defec

aircraft MSN 2403.

CHANGES

SUMMARY :

— MANPOWER

. Updated

— MATERIAL INFORMATION

. Kits A13R00 and D80R00 added.

PLANNING INFORMATION :

— EFFECTIVITY

. 1.A. Kits A13R00 and D80R00 added.

— DESCRIPTION

. 1.D. Installation of 2928VU added.

— MANPOWER
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

. 1.J. Updated.

MATERIAL INFORMATION :

— Material

. 2.A.(1) Sentence and address updated.

— LIST OF COMPONENTS

. 2.C. Kits A04R02, A06R02, A10R01, D42R03, D47R01, D49R01 

updated. Kits A13R00 and D80R00 added. Kit D83R01, Item 

— Consumable Materials

. 2.D.(1) Mat. No. 08-007B added.

ACCOMPLISHMENT INSTRUCTIONS :

— MODIFICATION

. 3.B.(1) Drawings 281145A00001 Sheet 01 thru Sheet 03 adde

. 3.B.(1)(e) Kit A13R00 and related drawing added. Drawings 

. 3.B.(1)(j) Placard set D9100095114295 becomes D9100095114

08-007B added. Drawings updated.

. 3.B.(1)(n) Bundle PN D9000095137995 becomes D900009513799

updated.

. 3.B.(1)(s)6 Drawings updated.

. 3.B.(5)(i) NOTE added.

. 3.B.(5)(bc) Work step added.

. 3.B.(5)(bk) Drawing D92891120000, Sheets 9 and 33 added.

. 3.B.(5)(bm)15 NOTE added.

— TESTS

. 3.C.(1)(d) Test for switching panel 2028VU added.

. 3.C.(1)(e) Test of CLS added.

2
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

Put this Revision Transmittal Sheet in front of the Service B

HISTORY OF PREVIOUS REVISIONS

No previous revisions.

REVISION SEQUENCE

ORIGINAL : Feb 28/06

REVISION No. : 01 — Apr 27/07

3
6 DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page : 1 of 

Printed in FRANCE © AIRBUS, 2007 All rights reserved

This summary is for information only

and is not approved for modification of the aircraf

ATA SYSTEM : 28

TITLE : FUEL - TANKS - INSTALL TWO ACT PROVISIONS WITH CLS CONFIG

MODIFICATION No. : 25415P4179 25696P4347 25713J1492 25713K4481 26

26110K4482 26138K4772 27446P5502 27447P5503 274

27717K5539 28068P5759 28661J2073 28817J1973 30

30356P7357 30373K6720 31110K7004 31143K7155 31

31812K7403 32261J2241 33198K8488 33199K8489 33

33492J2482 34742K9642 34758K9658 36348K10556 3

36350K10558 36399K6099

REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES

This Service Bulletin is issued in response to the request of a c

install the systems and structural provisions in the AFT cargo co

two Additional Center Tanks (ACT).

This Service Bulletin details the procedures to install systems a

structural provisions for two ACTs to be installed.

The accomplishment of this Service Bulletin and the installation 

ACTs will give the aircraft an increased operational range due to 

fuel capacity.

The operational/maintenance consequences of this Service Bulletin 

the update of the affected publications.

EVALUATION TABLE

COMPLIANCE Optional CANCELS INSPECTION S

POTENTIAL AD No A/C OPERATION AFFECT

RELIABILITY AFFECTED No PAX COMFORT AFFECTED 

COST SAVING No ETOPS AFFECTED 

NORMAL JACKING Yes VENDOR SB INVOLVED 

STRUCTURAL LIFE EXTN No DE-FUELING/VENTILATI

KIT PRICE (USD) See SB
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

As per EASA IR 21, a minor change is one that has no appreciable 

mass, balance, structural strength, reliability, operational char

affecting the airworthiness of the product. All other changes are 

EFFECTIVITY

This Service Bulletin is applicable to this (these) operator(s) :

62X

NOTE : This Service Bulletin is written for the operators listed 

modification in this Service Bulletin can be done by other 

If other operators want to do this modification, use the R

procedure and write to :

AIRBUS

CUSTOMER SERVICES DIRECTORATE

SC Department

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX

FRANCE

CONCURRENT REQUIREMENTS

None

REFERENCES/REPERCUSSIONS

TFU : None

OEB : None

AOT : None

SIL : None

LIFE LIMIT : None

LINE MAINTENANCE AFFECTED : No

OTHERS : None

NATURE OF THE WORK

AIRCRAFT : Yes

30373K6720 31110K7004 31143K7155 31700K7502 31

32261J2241 33198K8488 33199K8489 33373K8623 33

34742K9642 34758K9658 36348K10556 36349K10557 

36399K6099

2
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

Config. 01 , Kit 281145A01R01 thru Kit 281145A13R00

Config. 01 , Kit 281145B01R00 thru Kit 281145B04R00

Config. 01 , Kit 281145D01R00 thru Kit 281145D86R00

MATERIAL INFORMATION

AIRCRAFT DATA

Config. 01

Kit 281145A01R01

Plate, brackets, doublers, supports, fittings, loft drawing a

hardware.

Kit 281145A02R02

 Plates, brackets, rod, supports and related hardware.

Kit 281145A03R00

Canister, valves, pump, plate, insert, spring, pin, plug, bul

fairing, fittings, leads, actuator, switch and related hardwa

Kit 281145A04R02

Valve, sleeves, flange, elbows, strip, tee pieces, leads, uni

restrictors and related hardware.

Kit 281145A05R00

Elbows, plate, filter and related hardware.

TOTAL MANHOURS 2

ELAPSED TIME (HOURS) 1

TOTAL MANHOURS 

ELAPSED TIME (HOURS) 

TOTAL MANHOURS 19

ELAPSED TIME (HOURS) 3

3
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

Kit 281145A09R00

Placards.

Kit 281145A10R01

Brackets, bundles, modules, connectors, backshells, relays, b

conduits, mounts, spacer, placards and related hardware.

Kit 281145A11R03

Rack, modules, placards, connector, flange, base, retainer, r

related hardware.

Kit 281145A12R00

Control unit.

Kit 281145A13R00

Placards.

Kit 281145B01R00

Valves, filter, actuator and clamp.

Kit 281145B02R00

Panel and relay

Kit 281145B03R00

Panels

Kit 281145B04R00

Bundle

Kit 281145D01R00

Tube, leads and related hardware.

Kit 281145D02R00

Tube, strap, elbow and related hardware.

4
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

Kit 281145D05R00

Beam, struts, sections, angles, fittings, angles, plates, shim

connections, coupling and related hardware.

Kit 281145D06R00

Fittings, plates, sections, angles, shims, support, webs, key

cover, tubes, plugs, straps, x-beams and related hardware.

Kit 281145D07R00

Angles and related hardware.

Kit 281145D08R00

Pins and collars.

Kit 281145D10R00

Insulation blankets and strips.

Kit 281145D11R00

Brackets and related hardware.

Kit 281145D13R01

Tubes, flanges, sleeves, brackets, spacer, clamps, springs, l

related hardware.

Kit 281145D14R00

Monitor, tubes, hose, fitting, bracket, elbow, tee pieces, re

placards and related hardware.

Kit 281145D15R00

Monitor, tubes, hose, elbows, tee pieces, leads, placard and 

hardware.

Kit 281145D16R01

Tubes, inlet, filter, couplings, hoses, union, placards, elbow

straps and related hardware.

Kit 281145D17R00

5
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

Shield, shim and related hardware.

Kit 281145D20R00

Drain tubes and tee piece.

Kit 281145D25R00 thru Kit 281145D27R00

Panels.

Kit 281145D28R00

Panels and cover.

Kit 281145D31R00

Panels and related hardware.

Kit 281145D32R00

Cord and tape.

Kit 281145D33R00

Panels, plates, spacer and related hardware.

Kit 281145D34R00

Sections and cord.

Kit 281145D36R00

Sections, brackets, supports, plates and related hardware.

Kit 281145D40R01

X-beams, plates, fittings, sections, straps, filler, angles, 

cover, tubes, plugs, shims, bushings, rings and related hardw

Kit 281145D41R00

Pins and collars.

Kit 281145D42R03

Tracks, doubler, plates, shims, supports, blocks, latches and 

hardware.

6
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

Kit 281145D46R00

TDPs and related hardware.

Kit 281145D47R01

Sheets, mats, strips, band, tape and related hardware.

Kit 281145D48R00

Cable ties.

Kit 281145D49R01

Latch, tracks and related hardware.

Kit 281145D50R00

Latches.

Kit 281145D51R00

Placards strip and foil.

Kit 281145D52R00

Nets and stantion.

Kit 281145D61R00

Angles, plates, sheets, straps, wall, stiffeners, sections an

hardware.

Kit 281145D62R00 and Kit 281145D63R00

Pins and collars.

Kit 281145D70R00

Placards and cable ties.

Kit 281145D72R00

Placards.

Kit 281145D73R00

7
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

Overhead stowage compartments and related hardware.

Kit 281145D76R00

Flexible control assemblies, adaptors, sections, angles, brid

and related hardware.

Kit 281145D80R00

Panel, brackets and related hardware.

Kit 281145D82R01

Unions, tubes, bracket and related hardware.

Kit 281145D83R01

Brackets, sections, deflector, plate, sheet, angle and relate

Kit 281145D84R00

Brackets, mounts and related hardware.

Kit 281145D85R03

Brackets, mounts, sheets, conduit, connectors, supports, bobb

receptacles, placards, strap and related hardware.

Kit 281145D86R00

Harnesses and electrical equipment

APPENDICES

Appendix 1 - Leak test of the ACT shroud system and drain lines

8
6 DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page : 1 of 

Printed in FRANCE © AIRBUS, 2007 All rights reserved

ATA SYSTEM : 28

TITLE : FUEL - TANKS - INSTALL TWO ACT PROVISIONS WITH CLS CONFIG

MODIFICATION No. : 25415P4179 25696P4347 25713J1492 25713K4481 26

26110K4482 26138K4772 27446P5502 27447P5503 274

27717K5539 28068P5759 28661J2073 28817J1973 30

30356P7357 30373K6720 31110K7004 31143K7155 31

31812K7403 32261J2241 33198K8488 33199K8489 33

33492J2482 34742K9642 34758K9658 36348K10556 3

36350K10558 36399K6099

This document contains AIRBUS PROPRIETARY INFORMATION and shall a

remain the property of AIRBUS; no intellectual property right or 

granted by AIRBUS in connection with any information contained in 

delivered on the express condition that said document and the inf

contained in it shall be treated as confidential, shall not be us

purpose other than that for which it is hereby delivered. It shal

disclosed in whole or in part to third parties and shall not be d

any manner (except for the purposes of performing the tasks descr

and provided that any recipient of such document shall comply wit

conditions herein), without AIRBUS' prior written consent.

1. PLANNING INFORMATION

A. EFFECTIVITY

(1) Models

320-232

(2) Aircraft

(a) Effectivity by MSN

This Service Bulletin is applicable to aircraft 

2403

(b) Effectivity by Operator

The Operator/MSN relationship is provided for in

and is correct at the time of issue in accordan

information available to AIRBUS. Any future cha

from transfer of an aircraft from one operator t

not be reflected in this list unless the Service 

revised for another reason.
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

The kits and configurations applicable to these 

at the end of this list:

2403

KIT No. QTY PER A/C CONFIGURATION

281145A01R01 1 01

281145A02R02 1 01

281145A03R00 1 01

281145A04R02 1 01

281145A05R00 1 01

281145A06R02 1 01

281145A07R00 1 01

281145A08R00 1 01

281145A09R00 1 01

281145A10R01 1 01

281145A11R03 1 01

281145A12R00 1 01

281145A13R00 1 01

281145B01R00 1 01

281145B02R00 1 01

281145B03R00 1 01

281145B04R00 1 01

281145D01R00 1 01

281145D02R00 1 01

281145D03R00 1 01

281145D04R00 1 01

281145D05R00 1 01

281145D06R00 1 01

281145D07R00 1 01

281145D08R00 1 01

281145D10R00 1 01

281145D11R00 1 01

281145D13R01 1 01

281145D14R00 1 01

2
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

281145D19R00 1 01

281145D20R00 1 01

281145D25R00 1 01

281145D26R00 1 01

281145D27R00 1 01

281145D28R00 1 01

281145D31R00 1 01

281145D32R00 1 01

281145D33R00 1 01

281145D34R00 1 01

281145D36R00 1 01

281145D40R01 1 01

281145D41R00 1 01

281145D42R03 1 01

281145D43R00 1 01

281145D44R01 1 01

281145D46R00 1 01

281145D47R01 1 01

281145D48R00 1 01

281145D49R01 1 01

281145D50R00 1 01

281145D51R00 1 01

281145D52R00 1 01

281145D61R00 1 01

281145D62R00 1 01

281145D63R00 1 01

281145D70R00 1 01

281145D72R00 1 01

281145D73R00 1 01

281145D74R00 1 01

281145D75R00 1 01

281145D76R00 1 01

281145D80R00 1 01

3
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

NOTE : Config. 01 is valid for all the aircraft 

Service Bulletin as a standard configurat

(3) Spares

Config. 01

Door assy D5713019400200

Pipe assy D2821008001300

Computer SIC5059-11-0207

FQI 1407KID02-03

Fuel Quantity Indicator 1422KID-02-03

Placard D11311364A00

Placard D11311359A00

Integrally lighted plate 002098-05

Front plate D9251092000000

Plate D9251102000000

B. CONCURRENT REQUIREMENTS

None

C. REASON

(1) History

This Service Bulletin is issued in response to the r

customer to install the systems and structural provi

AFT cargo compartment for two Additional Center Tank

(2) Objective/Action

This Service Bulletin details the procedures to insta

the structural provisions for two ACTs to be install

(3) Advantages

The accomplishment of this Service Bulletin and the i

one or two ACTs will give the aircraft an increased o

range due to the increased fuel capacity.

281145D86R00 1 01

4
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

Operators must verify that all allowable damage lim

repairs performed (both in accordance with the SRM 

the SRM) are still applicable and effective to the 

Bulletin configuration. There may be a change or ad

maintenance requirements, such as temporary limits 

inspections, that apply in function of the Service 

configuration.

— If the post Service Bulletin status is not covered 

for repairs outside of the SRM, the operator should 

AIRBUS Customer Services Repair Engineering Support 

Repair review will be done by AIRBUS in accordance 

Customer Services Catalogue.

D. DESCRIPTION

To accomplish this Service Bulletin it is necessary to :

(1) Config. 01

(a) Install the doublers on the extrados, in the ce

(b) Install the brackets on the extrados, in the ce

(c) Install the bracket on the rear spar assy, in t

(d) Install the brackets on the intrados, in the ce

(e) Install the Additional Center Tank (ACT) door a

center tank

(f) Replace the Fuel Quantity Indicator (FQI) 6QT

(g) Modify the transfer line in the center tank

(h) Install the transfer elbow and the air ventilat

the center tank

(i) Apply the sealing protection to the center tank

(j) Modify the equipment and the wiring in the HYD/

(k) Modify the equipment and the wiring in the Rear 

121VU and the Rear Panel 120VU

(l) Modify the routing in the avionics compartment

5
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

(p) Modify the equipment and the wiring in the Relay 

(q) Modify the equipment and the wiring in the Conta

(r) Modify the equipment and the wiring in the AFT 

Rack 80VU

(s) Modify the equipment and the wiring in the FWD 

Rack 90VU

(2) Config. 01 , Kit 281145B01R00

(a) Install the equipment for the ACT pressurizatio

between FR48 and FR54.

(3) Config. 01 , Kit 281145B02R00

(a) Install the relay box in the forward avionics co

(4) Config. 01 , Kit 281145B02R00 , Kit 281145B03R00 and 

281145B04R00

(a) Remove and discard the refuel/defuel panel mount

in the belly fairing, zone 192.

(b) Install additional wiring between zone 192 and 

(c) Install the new refuel/defuel panel mounting as

belly fairing, zone 192.

(5) Config. 01

(a) Remove the inflation reservoirs 7506MM and 7507M

and RH offwing escape slides.

(b) In the AFT cargo compartment, remove the placard

inflation reservoir access.

(c) Install the MOD/SB placards.

(d) In the passenger compartment between FR41 and F

the harnesses 5339VB and 5340VB

(e) Between FR45 and FR48 (LH and RH), install the o

slide reservoirs and associated pressure tubes.

6
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

(i) Do the structural modification for the ACT 1 pro

AFT cargo compartment between FR48 and FR53.

(j) Do the structural modification for the ACT 2 pro

AFT cargo compartment between FR52 and FR54.

(k) Install the angles on the webs of the keel beam

and FR46

(l) Replace the fasteners at FR48, FR49, FR50 and F

STGR33 and STGR36 (LH).

(m) Replace the fasteners at FR52, FR53 and FR54, be

and STGR36 (LH).

(n) Replace the belly fairing panels 197AB and 198G

modification to the attachment structure.

(o) Do the modification to the passenger compartment 

structure between FR42 and FR46.

(p) Replace the fasteners between FR42 and FR44 (LH)

(q) Replace the fasteners between FR42 and FR44 (RH)

(r) In the AFT cargo compartment remove the ball mat

strips, the power drive units, the cargo nets an

32.

(s) Remove the roller tracks.

(t) Remove the servo mechanism and actuator.

(u) Remove the entrance guides, the YZ latch assemb

rail.

(v) Install the roller tracks and YZ latch assemblie

(w) Install the servo mechanism and actuator.

(x) Install the shim plates on the floor framework 

and FR59.

(y) Protect the roller tracks for corrosion.

7
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

(ac) Install the ball mats and ball strips between F

(ad) Install the X-latch, latch rail, guide rails and 

between FR53 and FR58.

(ae) Install the cargo nets in the AFT cargo compartm

(af) Remove the placards on the sidewall panels in t

compartment.

(ag) Install the placards on the sidewall panels in t

compartment.

(ah) After the adjustment of the roller tracks remove 

the XZ latches at FR50 and FR53.

(ai) Install the XZ latch 32ACT in the center roller 

and FR53.

(aj) Do the modification to the attachment structure 

cargo-compartment sidewall and partition panels

(ak) In the AFT cargo compartment replace the floor 

152SF, 151TF, 152TF, 151AG, 152AG, 151BG and 15

(al) Seal the gaps between the cargo compartment floo

151SF, 152SF, 151TF, 152TF, 151AG, 152AG, 151BG 

(am) Replace the insulation blankets between FR46 and 

(an) In the AFT cargo compartment, replace the ceili

151AC, 151BC and 151GC.

(ao) In the AFT cargo compartment, replace the sidewa

151CW, 151EW and 151HW.

(ap) In the AFT cargo compartment, replace the sidewa

152CW and 152DW.

(aq) In the AFT cargo compartment at FR47, replace t

panels 151BW, 151AW and 152BW.

(ar) In the passenger compartment, replace the floor 

251BF, 252BF, 252CF, 251GF, 251FF, 252GF and 25

8
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

(av) Install the ACT 1 cavity drain and monitoring sy

FR46 and FR50.

(aw) Install the ACT 1 pressurization system between 

(ax) Install the brackets for the fuel drain/vent sy

FR46 and FR54

(ay) Install the ACT 2 cavity drain and monitoring sy

FR50 and FR53.

(az) Install the ACT 2 pressurization system between 

(ba) Install the support brackets for the pressurizat

drain systems between FR51 and FR53

(bb) Install the beam between FR46 and FR47

(bc) Install the switching panel 2028VU.

(bd) Install the cover between FR46 and FR47 at the f

and vent lines.

(be) Replace the fuel drain line between FR42 and FR4

(bf) Do the modification to the support brackets on f

in the passenger compartment, between FR41 and 

between FR49 and FR55.

(bg) Replace the support bracket at FR42.

(bh) Do the modification to the support bracket insta

AFT cargo compartment between FR47 and FR55

(bi) Do the modification to the support bracket insta

between FR46 and FR52 and FR54.

(bj) Do the modification to the attachment parts for 

harnesses at FR42 and in the AFT cargo compartme

FR49 and FR55.

(bk) Do the modification to the attachment parts for 

harnesses at FR42.

(bl) Do the modification to the attachment parts for 

harnesses between FR46 and FR55.

9
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

(1) Classification

Optional

(2) Accomplishment Timescale

In accordance with operators' maintenance schedule.

F. APPROVAL

Approved under EASA Design Organisation Approval No. EASA

If an aircraft listed in the effectivity has a modificatio

embodied that is not of AIRBUS origin, and which affects 

this Service Bulletin, the operator is responsible for ob

approval by its airworthiness authority for any adaptatio

before incorporation of the Service Bulletin.

G. MANPOWER

The manpower estimates given in this Service Bulletin are 

direct labor cost to do the work. These estimates assume 

will be done by experienced personnel, and may need to be 

upwards to suit operator's circumstances. The estimates do 

the time to prepare, plan or inspect the work. Manufactur

procurement of parts and tools, drying times for paints, 

and general administration work are also not included.

Config. 01 , Kit 281145A01R01 thru Kit 281145A13R00

Get access 

Install the doublers on

the extrados

Install the brackets on

the extrados

Install the brackets on

the rear spar

Install the brackets on

the intrados

Install the ACT door assy 

Replace the FQI 

Modify the transfer line 

10
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

Config. 01 , Kit 281145B01R00 thru Kit 281145B04R00

Config. 01 , Kit 281145D01R00 thru Kit 281145D86R00

Modify the 121VU and 120VU 

Modify the routing 

Install the connectors

1975VC and 1982VC

Modify wiring in AVNCS and

cargo COMPT

Modify wiring in AVNCS and

cockpit

Modify the 103VU 

Modify the 107VU 

Modify the 80VU 

Modify the 90VU 

Test 

Close-up 

TOTAL MANHOURS 

ELAPSED TIME (HOURS) 

Get access 

Modification 

Close access 

TOTAL MANHOURS 

ELAPSED TIME (HOURS) 

Get access (including

jacking)

Removal of components 

Modification, Kit D01 

Modification, Kit D02 

Modification, Kit D03 

Modification, Kit D04 

Modification, Kit D05 1

Modification, Kit D06 2

11
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

Modification, Kit D14 

Modification, Kit D15 

Modification, Kit D16 

Modification, Kit D17 

Modification, Kit D18 

Modification, Kit D19 

Modification, Kit D20 

Modification, Kit D25 

Modification, Kit D26 

Modification, Kit D27 

Modification, Kit D28 

Modification, Kit D31 

Modification, Kit D32 

Modification, Kit D33 

Modification, Kit D34 

Modification, Kit D36 

Modification, Kit D40 4

Modification, Kit D41 

Modification, Kit D42 

Modification, Kit D43 

Modification, Kit D44 

Modification, Kit D46 

Modification, Kit D47 

Modification, Kit D48 

Modification, Kit D49 

Modification, Kit D50 

Modification, Kit D51 

Modification, Kit D52 

Modification, Kit D61 

Modification, Kit D62 

Modification, Kit D63 

Modification, Kit D70 

Modification, Kit D72 

12
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

H. WEIGHT AND BALANCE

Config. 01 , Kit 281145A01R01 thru Kit 281145A13R00

Manufacturers Empty Weight : +18.34 kg (+40.4323 lb)

Effect on Balance : +285.64 kgm (+2066.034 l

Kit 281145B01R00 thru Kit 281145B04R00

Not changed

Kit 281145D01R00

Manufacturers Empty Weight : +0.24 kg (+0.5291 lb)

Effect on Balance : +5.59 kgm (+40.432 lb.ft

Kit 281145D02R00

Manufacturers Empty Weight : +0.49 kg (+1.0802 lb)

Effect on Balance : +11.83 kgm (+85.566 lb.f

Kit 281145D03R00

Manufacturers Empty Weight : +0.22 kg (+0.4850 lb)

Effect on Balance : +5.28 kgm (+38.190 lb.ft

Kit 281145D04R00

Manufacturers Empty Weight : +16.05 kg (+35.3838 lb)

Modification, Kit D82 

Modification, Kit D83 

Modification, Kit D84 

Modification, Kit D85 2

Modification, Kit D86 3

Test 

Close up 

TOTAL MANHOURS 19

ELAPSED TIME (HOURS) 3

13
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

Kit 281145D06R00

Manufacturers Empty Weight : +11.36 kg (+25.0442 lb)

Effect on Balance : +281.73 kgm (+2037.753 l

Kit 281145D07R00

Manufacturers Empty Weight : +0.17 kg (+0.3747 lb)

Effect on Balance : +3.04 kgm (+21.988 lb.ft

Kit 281145D08R00

Manufacturers Empty Weight : +0.17 kg (+0.3747 lb)

Effect on Balance : +4.19 kgm (+30.306 lb.ft

Kit 281145D10R00

Manufacturers Empty Weight : -0.43 kg (-0.9480 lb)

Effect on Balance : -9.33 kgm (-67.484 lb.ft

Kit 281145D11R00

Manufacturers Empty Weight : +0.03 kg (+0.0661 lb)

Effect on Balance : +0.47 kgm (+3.399 lb.ft)

Kit 281145D13R01

Manufacturers Empty Weight : +23.30 kg (+51.3671 lb)

Effect on Balance : +454.35 kgm (+3286.313 l

Kit 281145D14R00

Manufacturers Empty Weight : +2.00 kg (+4.4092 lb)

Effect on Balance : +39.16 kgm (+283.244 lb

Kit 281145D15R00

Manufacturers Empty Weight : +1.15 kg (+2.5352 lb)

Effect on Balance : +25.27 kgm (+182.777 lb

14
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

Manufacturers Empty Weight : +1.21 kg (+2.6675 lb)

Effect on Balance : +26.50 kgm (+191.674 lb

Kit 281145D18R00

Manufacturers Empty Weight : +0.49 kg (+1.0802 lb)

Effect on Balance : +10.73 kgm (+77.610 lb.f

Kit 281145D19R00

Manufacturers Empty Weight : +1.02 kg (+2.2486 lb)

Effect on Balance : +21.52 kgm (+155.654 lb

Kit 281145D20R00

Manufacturers Empty Weight : +0.28 kg (+0.6172 lb)

Effect on Balance : +5.43 kgm (+39.275 lb.ft

Kit 281145D25R00

Manufacturers Empty Weight : +19.10 kg (+42.1078 lb)

Effect on Balance : +461.26 kgm (+3336.293 l

Kit 281145D26R00

Manufacturers Empty Weight : +3.80 kg (+8.3774 lb)

Effect on Balance : +92.24 kgm (+667.171 lb

Kit 281145D27R00

Manufacturers Empty Weight : -0.40 kg (-0.8819 lb)

Effect on Balance : -9.08 kgm (-65.676 lb.ft

Kit 281145D28R00

Manufacturers Empty Weight : +1.70 kg (+3.7478 lb)

Effect on Balance : +36.31 kgm (+262.630 lb

Kit 281145D31R00

15
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

Effect on Balance : +3.71 kgm (+26.834 lb.ft

Kit 281145D33R00

Manufacturers Empty Weight : +1.50 kg (+3.3069 lb)

Effect on Balance : +35.70 kgm (+258.218 lb

Kit 281145D34R00

Manufacturers Empty Weight : +1.70 kg (+3.7478 lb)

Effect on Balance : +41.31 kgm (+298.795 lb

Kit 281145D36R00

Manufacturers Empty Weight : +5.40 kg (+11.9048 lb)

Effect on Balance : +114.91 kgm (+831.144 lb

Kit 281145D40R01

Manufacturers Empty Weight : +16.75 kg (+36.9270 lb)

Effect on Balance : +448.23 kgm (+3242.047 l

Kit 281145D41R00

Manufacturers Empty Weight : +0.23 kg (+0.5070 lb)

Effect on Balance : +5.04 kgm (+36.454 lb.ft

Kit 281145D42R03

Manufacturers Empty Weight : +124.70 kg (+274.9136 lb

Effect on Balance : +2903.02 kgm (+20997.543 

Kit 281145D43R00

Manufacturers Empty Weight : +0.03 kg (+0.0661 lb)

Effect on Balance : +0.75 kgm (+5.424 lb.ft)

Kit 281145D44R01

Manufacturers Empty Weight : +11.70 kg (+25.7938 lb)

16
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

Kit 281145D47R01

Manufacturers Empty Weight : +27.14 kg (+59.8328 lb)

Effect on Balance : +693.70 kgm (+5017.532 l

Kit 281145D48R00

Not changed

Kit 281145D49R01

Manufacturers Empty Weight : +6.62 kg (+14.5944 lb)

Effect on Balance : +176.09 kgm (+1273.658 l

Kit 281145D50R00

Manufacturers Empty Weight : +9.60 kg (+21.1641 lb)

Effect on Balance : +226.94 kgm (+1641.457 l

Kit 281145D51R00

Manufacturers Empty Weight : +0.47 kg (+1.0361 lb)

Effect on Balance : +11.11 kgm (+80.358 lb.f

Kit 281145D52R00

Manufacturers Empty Weight : +9.80 kg (+21.6050 lb)

Effect on Balance : +239.61 kgm (+1733.099 l

Kit 281145D61R00

Manufacturers Empty Weight : +3.30 kg (+7.2751 lb)

Effect on Balance : +62.57 kgm (+452.568 lb

Kit 281145D62R00

Manufacturers Empty Weight : +0.34 kg (+0.7495 lb)

Effect on Balance : +6.46 kgm (+46.725 lb.ft

Kit 281145D63R00

17
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

Effect on Balance : +1.85 kgm (+13.381 lb.ft

Kit 281145D72R00

Not changed

Kit 281145D73R00

Manufacturers Empty Weight : +0.22 kg (+0.4850 lb)

Effect on Balance : +4.20 kgm (+30.378 lb.ft

Kit 281145D74R00

Manufacturers Empty Weight : +20.38 kg (+44.9297 lb)

Effect on Balance : +424.51 kgm (+3070.480 l

Kit 281145D75R00

Manufacturers Empty Weight : +1.20 kg (+2.6455 lb)

Effect on Balance : +11.40 kgm (+82.456 lb.f

Kit 281145D76R00

Manufacturers Empty Weight : -0.51 kg (-1.1244 lb)

Effect on Balance : -10.35 kgm (-74.862 lb.f

Kit 281145D80R00

Manufacturers Empty Weight : +0.850 kg (+1.8739 lb)

Effect on Balance : +26.095 kgm (+188.745 lb

Kit 281145D82R01

Manufacturers Empty Weight : +0.27 kg (+0.5952 lb)

Effect on Balance : +5.93 kgm (+42.891 lb.ft

Kit 281145D83R01

Manufacturers Empty Weight : +1.00 kg (+2.2046 lb)

Effect on Balance : +29.90 kgm (+216.266 lb

18
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

Manufacturers Empty Weight : +0.45 kg (+0.9920 lb)

Effect on Balance : +9.67 kgm (+69.943 lb.ft

Kit 281145D86R00

Manufacturers Empty Weight : +5.70 kg (+12.5662 lb)

Effect on Balance : +113.43 kgm (+820.439 lb

I. ELECTRICAL LOAD DATA

Not changed

19
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

23-12-00 23-44-00 

24-23-17 24-23-34 

24-23-55 24-24-00 

24-41-00 24-41-34 

25-21-41 25-23-41 

25-23-44 25-23-48 

25-28-41 25-52-00 

25-52-22 25-52-26 

25-52-44 25-52-48 

25-52-69 25-54-12 

25-55-11 25-55-41 

25-62-46 25-80-00 

26-13-00 26-17-00 

26-21-00 26-22-00 

27-34-00 27-51-00 

27-54-00 27-81-00 

27-92-15 27-92-16 

27-93-00 27-94-00 

27-96-00 28-00-00 

28-15-00 28-21-00 

28-23-00 28-24-00 

28-25-55 28-28-00 

28-42-00 28-42-21 

28-42-34 28-46-00 

29-10-00 29-11-00 

29-12-00 29-13-00 

29-14-00 29-19-51 

29-23-00 29-24-00 

29-32-00 29-33-11 

31-30-00 31-32-00 

31-50-00 31-55-34 

32-12-00 32-31-00 

32-33-00 32-33-17 

32-42-34 32-43-00 

32-45-00 32-46-00 

32-48-00 32-51-00 

33-13-00 33-14-00 

33-37-00 33-41-00 

33-48-00 33-51-00 

34-48-00 35-23-00 

36-12-00 49-61-34 

52-30-00 52-35-00 

53-22-14 53-32-12 

53-42-12 53-42-14 

73-25-34 74-00-00 

Consumable Material List (CML)

20
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

Process and Material Specification (PMS)

Standards Manual (SM)

Common Support Data Dictionary (CSDD) Chapter 2

Top Drawing, Issue C, Sheet 2 D00071141002

Appendix 1

DESIGN DRAWINGS SHEET(S)

281145A00001 01 A00

281145A00001 02 A00

281145A00001 03 B00

281145A01001 01 A00

281145A01001 02 A00

281145A01001 03 A00

281145A01002 01 A00

281145A01003 01 A00

281145A01003 02 A00

281145A01003 03 A00

281145A01003 04 A00

281145A01004 01 A00

281145A01004 02 A00

281145A01004 03 A00

281145A01005 01 A00

281145A02001 01 A00

281145A02002 01 A00

281145A02002 02 A00

281145A02002 03 A00

281145A02003 01 A00

281145A02003 02 A00

281145A03000 01 A00

281145A03001 01 A00

281145A03002 01 A00

281145A03002 02 A00

281145A03003 01 B00

281145A03004 01 A00

281145A03005 01 A00

21
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

281145A04001 03 A00

281145A04002 01 A00

281145A04002 02 A00

281145A04002 03 A00

281145A04002 04 A00

281145A04003 01 A00

281145A04003 02 A00

281145A04003 03 A00

281145A04003 04 A00

281145A04003 05 A00

281145A04004 01 A00

281145A04005 01 A00

281145A04006 01 A00

281145A04007 01 A00

281145A04008 01 A00

281145A04009 01 A00

281145A04010 01 A00

281145A04011 01 A00

281145A04011 02 A00

281145A04012 01 A00

281145A04013 01 A00

281145A05001 01 A00

281145A05002 01 A00

281145A05003 01 A00

281145A05003 02 A00

281145A06000 01 A00

281145A06001 01 A00

281145A06002 01 A00

281145A06003 01 B00

281145A06004 01 A00

281145A06005 01 A00

281145A06501 01 A00

281145A06501 02 A00

281145A06502 01 A00

281145A06502 02 A00

281145A06503 01 A00

281145A06503 02 A00

281145A06504 01 A00

22
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

281145A06507 01 A00

281145A06507 02 A00

281145A06508 01 A00

281145A06508 02 A00

281145A06509 01 A00

281145A06509 02 A00

281145A06510 01 A00

281145A06510 02 A00

281145A06511 01 A00

281145A06511 02 A00

281145A10001 01 A00

281145A10001 02 A00

281145A10002 01 A00

281145A10002 02 A00

281145A10003 01 A00

281145A10004 01 A00

281145A10004 02 A00

281145A10005 01 A00

281145A10005 02 A00

281145A10006 01 A00

281145A10006 02 A00

281145A10007 01 A00

281145A10007 02 A00

281145A10008 01 A00

281145A10008 02 A00

281145A10008 03 A00

281145A10009 01 A00

281145A10009 02 A00

281145A10010 01 A00

281145A10501 01 A00

281145A10501 02 A00

281145A10501 03 A00

281145A10501 04 A00

281145A10501 05 A00

281145A10501 06 A00

281145A10501 07 B00

281145A10501 08 A00

281145A10502 01 A00

23
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

281145A10502 07 B00

281145A10503 01 A00

281145A10503 02 A00

281145A10503 03 A00

281145A10503 04 A00

281145A10503 05 B00

281145A10503 06 A00

281145A10504 01 A00

281145A10504 02 A00

281145A10504 03 A00

281145A10504 04 A00

281145A10504 05 B00

281145A10504 06 A00

281145A10505 01 A00

281145A10505 02 A00

281145A10505 03 A00

281145A10505 04 B00

281145A10505 05 A00

281145A10506 01 A00

281145A10506 02 A00

281145A10506 03 A00

281145A10506 04 A00

281145A10506 05 B00

281145A10506 06 A00

281145A10507 01 A00

281145A10507 02 A00

281145A10507 03 A00

281145A10507 04 B00

281145A10507 05 A00

281145A10508 01 B00

281145A10508 02 A00

281145A10508 03 B00

281145A10509 01 A00

281145A10509 02 A00

281145A10509 03 B00

281145A10510 01 A00

281145A10510 02 A00

281145A10510 03 B00

24
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

281145A10513 02 A00

281145A10514 01 A00

281145A10514 02 A00

281145A10515 01 A00

281145A10515 02 A00

281145A10516 01 A00

281145A10516 02 A00

281145A10517 01 A00

281145A10517 02 A00

281145A10518 01 A00

281145A10518 02 A00

281145A10519 01 A00

281145A10519 02 A00

281145A10519 03 A00

281145A10519 04 B00

281145A10520 01 A00

281145A10520 02 A00

281145A10521 01 A00

281145A10521 02 A00

281145A10522 01 A00

281145A10522 02 A00

281145A11000 01 B00

281145A11001 01 A00

281145A11002 01 B00

281145A11003 01 A00

281145A11004 01 A00

281145A11004 02 A00

281145A13001 01 A00

D25286364014 7 and 8

D25288767000 1 and 2

D25571073000 1

D25571073002 2

D25571073004 3

D25571073006 4

D25572585000 1, 2, 7 and 23

D25572585002 3 - 5

D25572585004 6

D25572585006 8 - 10

25
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

D25572585022 31

D25572585024 32 and 33

D25572585026 28 and 29

D25572585028 34 and 35

D25572585030 40

D25572585032 38

D25572585034 36

D25572585036 37

D25572585038 39

D25573522000 1

D25573525006 13 - 16

D25670762000 1 - 7

D25671745000 1 - 7

D25671746000 1 - 4

D25690000004 7 - 9

D25870003048 20

D28270515000 1 - 4

D28270972002 7 - 12

D28270973002 6 - 10

D28270974002 4 - 6

D28270975 7 thru 12

D28270975004 8, 10, 11, 13 - 15

D28270982004 12 - 14, 17, 19, 20

26

D28270990002 2 and 4

D28270991000 1 - 3

D28270992000 1 - 4

D28270998002 2

D28270999004 3

D53370297002 1 - 7

D53370297003 1 - 7

D53370780004 2

D53371046000 1 - 5

D53371237000 1

D53371237001 1

D53372362006 1, 4 - 9 and 12 - 14

D53470075004 1 - 4, 6 - 17

D53470076004 1 - 10

26
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

D53675510000 1 - 3

D53675511000 1 - 3

D53975019000 1 - 6

D92355000 1

D92393242000 1

D92450032 6 and 7

D92450115 1 and 2

D92491681000 1 - 6

D92491681002 7 - 9

D92491681006 34 - 45

D92491681008 10, 12 - 24, 26, 27

48

D92492261000 1

D92550025 1

D92550032 1 and 2

D92556025 1 and 3

D92891120000 9 and 33

D92891805000 1 - 15

D92891805002 16 - 19

D92891805006 20, 22 - 31, 39 - 4

48, 50 - 52

D92894713062 1

D92894736004 14 - 17

D92991405000 1

D92991405001 2

D92991419005 6, H005

D92991419006 5, H006

D92991420005 6, H005

D92991420006 5, H006

D92991428013 18, H013

D92991428014 19, H014

D92991456004 5, H004

D92991456005 4, H005

D92991461021 26, H021

D92991461022 27, H022

D92991462010 10, H010

D92991462011 10, H004

D92991462011 11, H011

27
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

D92991471005 7, H005

D92991471006 8, H006

D92991472014 15, H014

D92991472016 16, H016

D92991473003 4, H003

D92991473004 3, H004

D92991475006 7, H006

D92991475007 8, H007

D92991480014 15, H014

D92991480015 16, H015

D92991481003 4, H003

D92991481004 5, H004

D92991483007 6, H007

D92991483008 7, H008

D92991492005 6, H005

D92991492006 7, H006

D92991493003 4, H003

D92991493004 3, H004

D92991494003 4, H003

D92991494004 3, H004

D92992293014 16

D92992293016 17

D92997026001 1 and 2

D92997026002 3 - 8

D92997028002 1 and 2

D92997028004 3 and 4

D92997028006 5 and 6

D92997028008 7 and 8

D92997043001 1 - 4

D92997043002 5 and 6

D92997043003 7 and 8

D92997043004 9 - 11

D92997043005 12 and 13

D92997043006 14 and 15

D92997043007 16 - 23

D93070516000 1 - 6

D93070668000 1 - 8

28
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

28-25-42 28-25-51 

28-25-58 28-28-11 

28-28-33 28-28-46 

28-28-53 28-40-00 

28-42-15 28-42-16 

28-42-22 28-43-00 

28-46-34 32-62-00 

57-17-11

Aircraft Schematic Manual (ASM) : 27-81-10 28-00-00 

28-21-00 28-25-00 

28-42-00 28-46-00 

33-14-00

Aircraft Wiring Lists (AWL)

Aircraft Wiring Manual (AWM) : 24-58-06 24-68-01 

24-68-04 24-68-05 

27-81-25 28-21-07 

28-25-04 28-25-08 

28-28-02 28-28-03 

28-42-15 28-42-16 

28-42-21 28-46-01 

28-46-14 28-46-15 

33-14-08 93-01-03 

93-01-21

Structural Repair Manual (SRM) : 57-11-11 57-11-29 

57-19-00

Trouble Shooting Manual (TSM) : 28-25-00 28-28-00 

28-46-00 32-31-00

29
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

This Service Bulletin has an operational impact. Please i

at least four weeks in advance, in case you need of your o

documentation to be amended by an intermediate revision p

embodiment.

For this purpose, please request the intermediate revision 

or mail to :

SDC3, AIRBUS - Customer Services Dire

Fax No. (33) 5 61 93 28 06

Sita No. TLSBP7X

E-mail sb.reporting@airbus.com

These amendments will be confirmed by the next normal rev

operational documentation, once your Service Bulletin acco

report has been sent, as usual, to our Customer Services 

(SDC3).

L. INTERCHANGEABILITY/MIXABILITY

NOTE : For definitions of interchangeability codes in col

to ATA Common Support Data Dictionary (CSDD), Chapt

28-22-03 28-25-03 

28-25-05 28-25-08 

28-28-03 28-28-04 

28-28-08 28-28-11 

28-28-33 28-28-51 

28-28-53 28-42-08 

28-46-08 29-12-03 

29-22-03 29-22-04 

29-32-03 31-14-11 

32-43-03 33-13-08 

33-51-04 53-16-01 

53-36-03 53-42-04 

53-49-04 57-11-05 

57-17-05 57-17-11

Master Minimum Equipment List (MMEL)

Flight Crew Operating Manual (FCOM) : Vol. 1

DESCRIPTION OLD PART No. NEW PART No. INT M

FQI 1407KID02-03 1418KID01-03 03 N

30
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

To facilitate the Material Kit reception, Airline Cu

requested to send a Customer Purchase Order to :

AIRBUS UPGRADE SERVICES

Attn FCO manager

Vendor parts are to be purchased from :

SMITHS AEROSPACE ELECTRONIC SYSTEMS

PO BOX 188

GL52 8SF CHELTENHAM

UNITED KINGDOM

(2) Price and Availability

Sales terms must be agreed between the Customers and 

accordance with the RFC (or RFC/RMO) procedure.

B. INDUSTRY SUPPORT INFORMATION

Refer to paragraph 2.A.(2): Price and Availability.

C. LIST OF COMPONENTS

Kit 281145A01R01

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM 

1 D5713304820004 Doubler 281145A01001 0

1 D5713031920000 Doubler 281145A01001 1

19 EN6115V3-3 Bolt 281145A01001 10

15 EN6115V3-4 Bolt 281145A01001 11

15 EN6115V3-5 Bolt 281145A01001 12

29 NSA5357-3-6 Pin 281145A01001 13

12 NSA5357-3-7 Pin 281145A01001 14

16 NSA5357-3-5 Pin 281145A01001 15

8 NSA5357-4-7 Pin 281145A01001 22

5 NSA5357-4-8 Pin 281145A01001 23

57 NSA5330-6 Nut 281145A01001 30

49 ASNA2528-3 Nut 281145A01001 35

13 NSA5330-8 Nut 281145A01001 40

1 D5791332400000 Bracket 281145A01002 0

1 D5791332300000 Bracket 281145A01002 1

31
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

NOTE : Refer to the AIRBUS Standards Manual (SM) if you f

numbers of hardware components in the related kit(

cannot identify in the LIST OF COMPONENTS of this 

1 D5791048300095 Fitting 281145A01003 3

1 D5791048200095 Fitting 281145A01003 4

1 D5791042020095 Fitting 281145A01003 5

1 D5791042120095 Fitting 281145A01003 6

1 D5791043020095 Fitting 281145A01003 9

1 D5791049820095 Fitting 281145A01003 10

1 D5791050020095 Fitting 281145A01003 11

1 D5791042320095 Support 281145A01003 12

1 D5791042220095 Support 281145A01003 13

2 A2823301800202 Plate 281145A01003 21

4 ASNA2050DCJ3215 Rivet 281145A01003 22

6 NSA5357-3-5 Pin 281145A01003 100

8 NSA5357-3-7 Pin 281145A01003 102

4 NSA5357-3-8 Pin 281145A01003 103

4 NSA5357-3-10 Pin 281145A01003 104

4 NSA5357-4-7 Pin 281145A01003 107

8 NSA5357-4-8 Pin 281145A01003 108

2 NSA5357-4-9 Pin 281145A01003 109

4 NSA5357-4-10 Pin 281145A01003 110

22 NSA5330-6 Nut 281145A01003 120

18 NSA5330-8 Nut 281145A01003 130

1 D5791041820095 Support 281145A01004 0

2 NSA5357-4-11 Pin 281145A01004 60

2 NSA5357-5-13 Pin 281145A01004 65

2 NSA5330-8 Nut 281145A01004 75

2 NSA5330-10 Nut 281145A01004 80

1 D2821334100300 Rod 281145A01005 0

1 D2821334220000 Bracket 281145A01005 4

4 NAS6603-4 Bolt 281145A01005 12

2 NAS6604-9 Bolt 281145A01005 14

4 NSA5050-3 Nut 281145A01005 20

2 NSA5050-4 Nut 281145A01005 22

4 ASNA2397-10L Washer 281145A01005 24

2 ASNA2397-416L Washer 281145A01005 26

1 D5713032000095 Loft

32
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

NOTE : Refer to the AIRBUS Standards Manual (SM) if you f

numbers of hardware components in the related kit(

cannot identify in the LIST OF COMPONENTS of this 

Bulletin. The SM will give you the correct part num

number relationship.

Kit 281145A03R00

2 ASNA2050DCJ3215 Rivet 281145A02001 32

1 D5791040320095 Bracket 281145A02002 1

1 D5791040500095 Support 281145A02002 2

1 D5791040400095 Support 281145A02002 3

1 D5791040120095 Bracket 281145A02002 4

1 D5791040020295 Bracket 281145A02002 5

1 D5791040220095 Bracket 281145A02002 6

1 D5791040820095 Bracket 281145A02002 7

1 D5791040920095 Bracket 281145A02002 8

1 D5791040620095 Bracket 281145A02002 9

1 D5791040720095 Bracket 281145A02002 10

1 D5791041020095 Bracket 281145A02002 11

4 NAS6603-4 Bolt 281145A02002 44

4 NSA5050-3 Nut 281145A02002 62

8 NSA5357-4-9 Pin 281145A02002 157

5 NSA5357-4-10 Pin 281145A02002 158

17 NSA5357-4-11 Pin 281145A02002 159

1 NSA5357-4-12 Pin 281145A02002 160

1 NSA5357-5-13 Pin 281145A02002 162

31 NSA5330-8 Nut 281145A02002 165

1 NSA5330-10 Nut 281145A02002 170

1 D2821334100400 Rod 281145A02003 2

1 D2821040220000 Bracket 281145A02003 6

1 D2821040120000 Plate 281145A02003 8

8 NAS6603-2 Bolt 281145A02003 10

4 NAS6603-4 Bolt 281145A02003 12

2 NAS6604-9 Bolt 281145A02003 14

4 NSA5050-3 Nut 281145A02003 20

2 NSA5050-4 Nut 281145A02003 22

12 ASNA2397-10L Washer 281145A02003 24

2 ASNA2397-416L Washer 281145A02003 26

33
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

1 D5713323000000 Door 281145A03002 4

8 A5713052120300 Washer 281145A03002 6

3 NAS6603-2 Bolt 281145A03002 10

15 ABS0114V4-18 Bolt 281145A03002 11

4 ASNA2397D10L Washer 281145A03002 15

15 MS20002C4 Washer 281145A03002 16

1 NAS6603-3 Bolt 281145A03002 20

6 NAS6604-3 Bolt 281145A03002 22

6 ASNA2397D416L Washer 281145A03002 40

1 HTE690045 Switch 281145A03004 0

1 D2821067800000 Bulkhead 281145A03004 8

1 A2823260820000 Plug 281145A03004 10

1 A2823260500000 Valve 281145A03004 12

3 NSA8200-6 O-Ring 281145A03004 18

1 NSA8203-019 O-Ring 281145A03004 20

4 NAS6603-5 Bolt 281145A03004 22

4 ASNA2055-03 Washer 281145A03004 24

4 NSA5050-3 Nut 281145A03004 26

30 cm MS20995C32 Wire 281145A03004 28

1 568-1-27170-002 Pump 281145A03005 0

1 568-1-27171-002 Plate 281145A03005 2

1 A2821064820040 Pin 281145A03005 10

1 A2821064620000 Insert 281145A03005 12

1 A2821064720000 Spring 281145A03005 14

1 NSA8203-113 O-Ring 281145A03005 18

1 NSA8203-167 O-Ring 281145A03005 22

1 NSA8203-224 O-Ring 281145A03005 24

1 NSA8203-226 O-Ring 281145A03005 26

2 E0088-10-100 Lead 281145A03005 28

4 NAS6603-1 Bolt 281145A03005 29

6 NAS6604-7 Bolt 281145A03005 30

1 NAS6604-20 Bolt 281145A03005 32

1 NSA5112-04 Washer 281145A03005 34

6 ASNA2397-416 Washer 281145A03005 36

1 ASNA2397-416L Washer 281145A03005 38

4 ASNA2397D10L Washer 281145A03005 39

1 NSA5050-4 Nut 281145A03005 40

2 NSA5050-3 Nut 281145A03005 42

34
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

NOTE : For definitions of interchangeability codes in col

to ATA Common Support Data Dictionary (CSDD), Chapt

NOTE : Refer to the AIRBUS Standards Manual (SM) if you f

numbers of hardware components in the related kit(

cannot identify in the LIST OF COMPONENTS of this 

Bulletin. The SM will give you the correct part num

number relationship.

Kit 281145A04R02

1 NAS1801-06-6 Screw 281145A03006 10

1 NAS1801-3-6 Screw 281145A03006 11

1 ASNA2397-6L Washer 281145A03006 12

1 ASNA2397-10L Washer 281145A03006 13

1 MS21042-06 Nut 281145A03006 14

4 NAS1726C4E Nut 281145A03006 16

1 E0088-16-125 Lead 281145A03006 22

1 HTE900135 Valve 281145A03007 0

1 HTE190001-2 Actuator 281145A03007 2

1 HTE8002 Clamp 281145A03007 4

1 NSA8203-154 O-Ring 281145A03007 6

6 NAS1153-4 Screw 281145A03007 8

1 NAS1801-06-6 Screw 281145A03007 13

4 NAS1726C4E Nut 281145A03007 16

1 ASNA2397-6L Washer 281145A03007 17

1 MS21042L06 Nut 281145A03007 18

1 E0088-16-100 Lead 281145A03007 22

40 cm MS20995C32 Wire 281145A03007 24

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM 

4 NSA8203-226 O-Ring 281145A04002 5

1 D2821333900000 Pipe 281145A04002 6

1 NAS6603-3 Bolt 281145A04002 9

1 ASNA2397JD10L Washer 281145A04002 10

1 ASNA2397-10L Washer 281145A04002 11

1 D2821333900100 Pipe 281145A04002 12

3 NAS6603-2 Bolt 281145A04002 16

2 NAS1726-3E Nut 281145A04002 18

35
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

1 D2821333900300 Pipe 281145A04003 22

1 D2821333900400 Pipe 281145A04003 24

1 D2821333900600 Pipe 281145A04003 28

1 D2821333900700 Pipe 281145A04003 30

1 D2821333901000 Pipe 281145A04003 32

1 A2821038600000 Sleeve 281145A04003 34

1 D2821333800000 Sleeve 281145A04003 36

1 D2821334800200 Pipe 281145A04003 38

1 D2821334900200 Pipe 281145A04003 40

1 D2821335000200 Pipe 281145A04003 42

1 D2821338500000 Pipe 281145A04003 44

1 D2821335800200 Pipe 281145A04003 46

1 D2821336720240 RSTRCTR 281145A04003 50

1 NSA5516A04NF Clamp 281145A04003 51

1 MS21902D4 Union 281145A04003 52

1 ASNA0182-1DA Strip 281145A04003 53

2 ABS0107-150 Nut 281145A04003 55

2 ABS0107-200 Nut 281145A04003 56

2 NSA840003-150 Ring 281145A04003 57

2 NSA840003-200 Ring 281145A04003 58

1 NSA8200-4 O-Ring 281145A04003 60

1 NSA8203-215 O-Ring 281145A04003 62

12 NSA8203-222 O-Ring 281145A04003 64

4 NSA8203-226 O-Ring 281145A04003 66

2 NAS1801-06-10 Screw 281145A04003 68

14 NAS6603-2 Bolt 281145A04003 70

4 NAS6603-4 Bolt 281145A04003 72

4 NAS6603-5 Bolt 281145A04003 73

4 NAS6603-3 Bolt 281145A04003 74

2 NAS6604-2 Bolt 281145A04003 76

4 NAS6604-3 Bolt 281145A04003 77

2 MS21042L06 Nut 281145A04003 78

19 NSA5050-3 Nut 281145A04003 80

6 NSA5050-4 Nut 281145A04003 82

2 ASNA2397-6L Washer 281145A04003 83

7 ASNA2397-10L Washer 281145A04003 84

2 E0088-10-160 Lead 281145A04003 90

1 E0088-10-200 Lead 281145A04003 92

36
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

1 D2821332220000 Elbow 281145A04005 0

2 NAS6604-4 Bolt 281145A04005 10

2 ASNA2397-416L Washer 281145A04005 12

2 NAS1726-4E Nut 281145A04005 14

1 A2821120120000 Elbow 281145A04006 0

2 NAS6604-4 Bolt 281145A04006 10

2 ASNA2397-416L Washer 281145A04006 12

2 NAS1726-4E Nut 281145A04006 14

1 D2821332620000 Elbow 281145A04007 0

2 NAS6604-5 Bolt 281145A04007 10

2 ASNA2397-416L Washer 281145A04007 12

2 NAS1726-4E Nut 281145A04007 14

1 D2821339020000 Elbow 281145A04008 0

1 NSA8203-226 O-Ring 281145A04008 8

4 NAS6603-4 Bolt 281145A04008 10

4 ASNA2397D10L Washer 281145A04008 12

1 D2821333220000 Elbow 281145A04009 0

1 D2821333420000 Elbow 281145A04009 2

1 D2821336621240 RSTRCTR 281145A04009 4

2 NSA8203-222 O-Ring 281145A04009 8

8 NAS6603-3 Bolt 281145A04009 10

8 ASNA2397-10L Washer 281145A04009 12

1 9843144M Valve 281145A04010 0

1 A2821079520000 Flange 281145A04010 1

1 D2821335621800 RSTRCTR 281145A04010 2

1 ABS0107-200 Nut 281145A04010 3

1 NSA840003-200 Ring 281145A04010 4

3 NSA8203-226 O-Ring 281145A04010 5

4 NAS6604-12 Bolt 281145A04010 8

4 NAS1726-4E Nut 281145A04010 9

2 E0088-10-100 Lead 281145A04010 11

2 NAS1726-3E Nut 281145A04010 12

1 NAS6603-2 Bolt 281145A04010 13

1 NAS6603-1 Bolt 281145A04010 14

2 ASNA2397-10L Washer 281145A04010 19

1 D2821336300000 Sleeve 281145A04011 35

1 365A02 Valve 281145A04011 54

2 ABS0107-150 Nut 281145A04011 55

37
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

NOTE : For definitions of interchangeability codes in col

to ATA Common Support Data Dictionary (CSDD), Chapt

NOTE : Refer to the AIRBUS Standards Manual (SM) if you f

numbers of hardware components in the related kit(

cannot identify in the LIST OF COMPONENTS of this 

Bulletin. The SM will give you the correct part num

number relationship.

Kit 281145A05R00

1 D2821331320000 Tee 281145A04012 0

4 NAS6604-5 Bolt 281145A04012 10

4 ASNA2397-416L Washer 281145A04012 12

4 NAS1726-4E Nut 281145A04012 14

1 D2821331920000 Elbow 281145A04013 0

1 D2821336500000 Sleeve 281145A04013 2

2 NSA8203-222 O-Ring 281145A04013 8

4 NAS6603-7 Bolt 281145A04013 10

4 ASNA2397-416L Washer 281145A04013 12

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM 

1 D2821330700000 Elbow 281145A05001 0

1 D2821334700000 Nutplate 281145A05001 2

1 D2821337500000 Nutplate 281145A05001 4

1 NSA8203-148 O-Ring 281145A05001 8

6 NAS6604-9 Bolt 281145A05001 10

6 ASNA2397-416L Washer 281145A05001 12

1 NAS6603-2 Bolt 281145A05001 14

1 ASNA2397-10L Washer 281145A05001 16

1 D2821337700041 Elbow 281145A05002 0

1 D2821334600000 Nutplate 281145A05002 2

1 D2821337600000 Nutplate 281145A05002 4

1 NSA8203-152 O-Ring 281145A05002 8

6 NAS6604-8 Bolt 281145A05002 10

6 ASNA2397-416L Washer 281145A05002 12

1 D2821337800000 Filter 281145A05002 14

1 D2821337120000 Plate 281145A05002 16

4 NAS6603-2 Bolt 281145A05002 18

38
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

NOTE : Refer to the AIRBUS Standards Manual (SM) if you f

numbers of hardware components in the related kit(

cannot identify in the LIST OF COMPONENTS of this 

Bulletin. The SM will give you the correct part num

number relationship.

Kit 281145A06R02

NOTE : Refer to the AIRBUS Standards Manual (SM) if you f

numbers of hardware components in the related kit(

cannot identify in the LIST OF COMPONENTS of this 

Bulletin. The SM will give you the correct part num

number relationship.

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM 

4 NAS1102-06-7 Screw 281145A06003 14

1 NAS1102-08-7 Screw 281145A06003 15

2 NAS1102-06-5 Screw 281145A06003 16

5 ASNA2083BG2-10 Screw 281145A06003 17

28 NAS1102-04-6 Screw 281145A06003 18

1 MS21042-08 Nut 281145A06003 21

1 ASNA2397-8L Washer 281145A06003 24

1 E0417C01S CNCTR 281145A06003 31

1 E0416-02 Sleeve 281145A06003 32

1 E0415C3LM078E Switch 281145A06003 33

1 D1131043320100 Placard 281145A06004 4

1 D1131043320200 Placard 281145A06004 6

3 NSA931320-030 C/B 281145A06005 1

4 NSA931320-050 C/B 281145A06005 2

1 NSA931322-100 C/B 281145A06005 3

20 E0736N08-01 Screw 281145A06005 4

20 ASNA2553-0401 Washer 281145A06005 5

8 ABS0772A02A Clamp 281145A06005 6

10 ASNA2080G04 Button 281145A06005 9

1 D9000095128395 Bundle

1 D9100095114296 PLCRDSET

150 NSA935401-03 Tie

150 NSA935401-06 Tie

2 NSA939526-02 Shunt

39
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

to ATA Common Support Data Dictionary (CSDD), Chapt

Kit 281145A08R00

Kit 281145A09R00

Kit 281145A10R01

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM 

1 D9251314900000 Plate 281145A06003 0

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM 

1 D11311658A00 Placard 281145A06005 7

1 D11311361A00 Placard 281145A06005 8

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM 

1 E0661-21 Mount 281145A10002 1

4 E0420-04 Stud 281145A10002 2

1 ABS0355-02 Bracket 281145A10002 3

2 E0661-22 Mount 281145A10002 5

1 D9241244120000 Bracket 281145A10003 1

1 NSA5527-03-01 Spacer 281145A10003 2

1 NAS1801-3-20 Screw 281145A10003 3

2 NSA935504-01 Mount 281145A10003 4

1 NAS1726-3E Nut 281145A10003 5

2 ASNA2051DCJ3215 Rivet 281145A10003 18

1 D5391047900001 Bracket 281145A10004 0

2 ASNA2050DCJ3215 Rivet 281145A10004 6

1 NSA935504-03 Mount 281145A10005 0

2 NSA935504-01 Mount 281145A10005 2

3 NAS1801-3-8 Screw 281145A10005 4

3 ASNA2397-10L Washer 281145A10005 6

5 NAS1801-3-9 Screw 281145A10006 10

5 ASNA2397-10L Washer 281145A10006 11

5 NAS1726-3E Nut 281145A10006 14

1 EN3646A62041BN CNCTR 281145A10006 20

1 EN3646A61419BN CNCTR 281145A10006 21

1 E0080-01-20C BACKSHLL 281145A10006 22

40
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

1 E0427-01A Retainer 281145A10008 1

1 NAS1100-04-6 Screw 281145A10008 2

1 ASNA2397-4L Washer 281145A10008 4

1 ASNA2397-3L Washer 281145A10008 5

5 MS21042L04 Nut 281145A10008 6

1 E0245-28A0 Relay 281145A10008 40

1 E0250A0S Base 281145A10008 41

1 E0666D28A0 Relay 281145A10008 50

1 E0247A0S Base 281145A10008 51

3 ASNA2397-4L Washer 281145A10009 4

3 MS21042L04 Nut 281145A10009 6

3 NAS1100-04-7 Screw 281145A10009 8

1 EN3545D03FXA22A CNCTR 281145A10009 50 

1 EN3545D03MXB22A CNCTR 281145A10009 51 

2 EN3545-007SCD BACKSHLL 281145A10009 52

1 NSA937901MA2008 Module 281145A10009 60

1 NSA937901E1 IDENT 281145A10009 61

1 NSA937901E0 IDENT 281145A10009 62

1 NSA932843AA01 Relay 281145A10009 70

1 NSA932844AA Base 281145A10009 71

1 NSA937901MA2206 Module 281145A10010 0

2 NSA937901E2 IDENT 281145A10010 1

1 NSA937901E8 IDENT 281145A10010 2

1 NSA937901MA2204 Module 281145A10010 3

1 NSA937901E6 IDENT 281145A10010 4

1 D9000095137395 Bundle

1 D9000095137495 Bundle

1 D9000095137595 Bundle

1 D9000095137695 Bundle

1 D9000095137795 Bundle

1 D9000095137895 Bundle

1 D9000095137996 BUNDLE

1 D9000095138095 Bundle

1 D9100095116795 PLCRDSET

100 NSA935401-03 Tie

360 NSA935401-04 Tie

300 NSA935401-05 Tie

41
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

() pp

NOTE (03) PN supplied with reference EN3545D03FXA00A.

NOTE (04) PN supplied with reference EN3545D03MXB00A.

NOTE : Refer to the AIRBUS Standards Manual (SM) if you f

numbers of hardware components in the related kit(

cannot identify in the LIST OF COMPONENTS of this 

Bulletin. The SM will give you the correct part num

number relationship.

Kit 281145A11R03

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM 

3 NAS1102-3-10 Screw 281145A11002 4

1 D9251116900000 Plate 281145A11002 7

3 NAS1801-3-8 Screw 281145A11002 12

5 NSA939511-03 Cover 281145A11002 15

6 NSA5050-3 Nut 281145A11002 16

3 ASNA2397-10L Washer 281145A11002 28

1 NSA937901MA2204 Module 281145A11002 50

1 NSA937901MA2011 Module 281145A11002 51

3 NSA937901E2 IDENT 281145A11002 52

1 NSA937901E1 IDENT 281145A11002 53

1 E0425A2001 Module 281145A11002 55

2 D9251127600000 Flange 281145A11003 0

1 D0003006100000 Rack 281145A11003 1

1 E0161D01A12X CNCTR 281145A11003 3 

4 NAS1100-06-12 Screw 281145A11003 6

4 NAS1100-04-7 Screw 281145A11003 9

2 ASNA2397-6L Washer 281145A11003 12

4 ASNA2397-4L Washer 281145A11003 14

1 E0427-01A Retainer 281145A11004 1

1 NAS1100-04-6 Screw 281145A11004 2

1 ASNA2397-4L Washer 281145A11004 4

1 ASNA2397-3L Washer 281145A11004 5

3 MS21042L04 Nut 281145A11004 6

1 E0247A0S Base 281145A11004 40

42
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

() y

numbers of hardware components in the related kit(

cannot identify in the LIST OF COMPONENTS of this 

Bulletin. The SM will give you the correct part num

number relationship.

Kit 281145A12R00

NOTE : For definitions of interchangeability codes in col

to ATA Common Support Data Dictionary (CSDD), Chapt

Kit 281145A13R00

Kit 281145B01R00

Kit 281145B02R00

Kit 281145B03R00

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM 

1 30042-0000-0501 CTL UNIT 281145A11002

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM 

1 D2821336920000 PLACARD 281145A13001 0

1 D2821336920200 PLACARD 281145A13001 2

1 D2821336920400 PLACARD 281145A13001 4

1 D2821336920600 PLACARD 281145A13001 6

1 D2821336920800 PLACARD 281145A13001 8

ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. 

41 QB0566 1 Filter

42 HTE490005 2 Valve

43 HTE200002-1 1 Actuator

44 HTE920007-001 1 Valve

45 HTE8002 1 Clamp

46 PAS148-133A 1 Valve

ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. 

D9255002500200 1 Panel

D9255602500400 1 Relay

43
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

Kit 281145D01R00

NOTE : Refer to the AIRBUS Standards Manual (SM) if you f

numbers of hardware components in the related kit(

cannot identify in the LIST OF COMPONENTS of this 

Bulletin. The SM will give you the correct part num

number relationship.

Kit 281145D02R00

ITEM NEW PART No. QTY UM KEYWORD ITEM OLD PART No. 

D92400000647 1 Bundle

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM 

1 D2827097702200 TUBE D28279990002 0006

3 MS21919WDE8 CLAMP D28270990002 0014

1 NAS1096-3-9 SCREW D28270990002 0015

4 NAS1096-3-8 SCREW D28270990002 0016

5 NAS1149C0332R WASHER D28270990002 0017

5 NAS1291C3M NUT D28270990002 0049

2 NSA5519-11 CLAMP D28270990002 0051

2 E0090-10-160NN LEAD D28270990002 0061

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM 

1 D2827097902600 TUBE D28270991000 0000

1 AN924-10J NUT D28270991000 0034

1 NAS1149C1432R WASHER D28270991000 0035

1 NAS1726C3E NUT D28270991000 0070

1 NAS1149C0332R WASHER D28270991000 0073

1 MS21919WDE10 CLAMP D28270991000 0079

1 NSA5575-8A CLAMP D28270991000 0081

1 E0090-10-125NN LEAD D28270991000 0083

1 NAS1303-2 BOLT D28270991000 0088

1 NAS1726-3E NUT D28270991000 0089

1 NAS1149D0316H WASHER D28270991000 0090

1 MS21908J10 ELBOW D28270991000 0091

1 NAS1096-3-9 SCREW D28270991000 0097

44
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

NOTE : Refer to the AIRBUS Standards Manual (SM) if you f

numbers of hardware components in the related kit(

cannot identify in the LIST OF COMPONENTS of this 

Bulletin. The SM will give you the correct part num

number relationship.

Kit 281145D04R00

NOTE : Refer to the AIRBUS Standards Manual (SM) if you f

numbers of hardware components in the related kit(

cannot identify in the LIST OF COMPONENTS of this 

Bulletin. The SM will give you the correct part num

number relationship.

Kit 281145D05R00

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM 

1 D2827098324800 BRACKET D28270992000 0002

2 D2827098325000 BRACKET D28270992000 0004

1 D2827098325200 BRACKET D28270992000 0006

10 LN9198-4012CF RIVET D28270992000 0040

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM 

1 D5347503400200 PANEL D53475024000 0000

1 D5347505400200 FAIRING D53475024000 0002

1 D5347505600400 COVER D53475024000 0004

1 D5347521520000 SECTION D53475024000 0006

1 D5347542400000 BRACKET D53475024000 0008

2 D5347542720000 BRACKET D53475024000 0010

1 D5347542400200 BRACKET D53475024000 0012

1 D5347521120000 BRACKET D53475024000 0014

1 D5347521920000 ANGLE D53475024000 0016

11 ABS0368-01 RECEPTCL D53475024000 0028

5 NAS1791A3-1 NUT D53475024000 0030

2 D5347521320000 WASHER D53475024000 0032

32 DIN65399-2406BF RIVET D53475024000 0125

57 LN9198-4009CF RIVET D53475024000 0240

45
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

1 D5337219220100 FITTING D53372362006 0009

1 D5337219120200 FITTING D53372362006 0010

1 D5337219120300 FITTING D53372362006 0011

1 D5337219020200 FITTING D53372362006 0012

1 D5337215920000 ANGLE D53372362006 0014

8 D5337215920200 ANGLE D53372362006 0016

1 D5337215920400 ANGLE D53372362006 0018

1 D5337215920500 ANGLE D53372362006 0019

1 D5337215920600 ANGLE D53372362006 0020

1 D5337217320000 PLATE D53372362006 0022

1 D5337217400000 PLATE D53372362006 0024

1 D5337217400100 PLATE D53372362006 0025

1 D5337216020090 SECTION D53372362006 0026

1 D5347449520800 SECTION D53372362006 0028

1 D5347449520900 SECTION D53372362006 0029

1 D5337601520600 SHIM D53372362006 0030

1 D5337601520800 SHIM D53372362006 0032

1 D5337601521000 SHIM D53372362006 0034

1 D5337601521200 SHIM D53372362006 0036

1 D5337601521400 SHIM D53372362006 0038

1 D5347100720600 COUPLING D53372362006 0040

1 D5347101620490 CONNECTN D53372362006 0042

1 D5347101620590 CONNECTN D53372362006 0043

3 D5337602020000 SECTION D53372362006 0044

3 D5337602020100 SECTION D53372362006 0045

4 NAS1791A3-1 NUT D53372362006 0046

1 D5347100920090 SUPPORT D53372362006 0048

1 D5347100920190 SUPPORT D53372362006 0049

1 D5347104120090 ANGLE D53372362006 0050

1 D5347104120190 ANGLE D53372362006 0051

4 D5337236220400 SHIM D53372362006 0052

1 D5337036520200 ANGLE D53372362006 0150

1 D5337036520300 ANGLE D53372362006 0151

2 D5347007422000 ANGLE D53372362006 0152

2 D5347007422100 ANGLE D53372362006 0153

2 D5347007422200 ANGLE D53372362006 0156

12 ASNA0082A302 BOLT D53372362006 0435

2 ASNA0082A303 BOLT D53372362006 0436

46
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

2 MS20002C9 WASHER D53372362006 0468

4 MS21250-06018 BOLT D53372362006 0470

4 NAS1726-6E NUT D53372362006 0472

4 MS20002C6 WASHER D53372362006 0474

12 NAS1097AD3-10 RIVET D53372362006 0524

12 NAS1097AD4-10 RIVET D53372362006 0532

98 NAS1097AD5-10 RIVET D53372362006 0540

8 DAN7-6-6X PIN D53372362006 0566

200 LN9198-4010CF RIVET D53372362006 0640

61 LN9198-4810CF RIVET D53372362006 0648

4 LN9198-5610CF RIVET D53372362006 0656

12 DAN5-6-4X PIN D53372362006 0764

8 DAN5-6-5X PIN D53372362006 0765

16 DAN5-6-6X PIN D53372362006 0766

24 DAN5-6-7X PIN D53372362006 0767

86 DAN5-6-8X PIN D53372362006 0768

20 DAN5-6-9X PIN D53372362006 0769

4 DAN5-6-10X PIN D53372362006 0770

12 DAN5-6-11X PIN D53372362006 0771

12 DAN5-6-12X PIN D53372362006 0772

68 NSA5075-5 COLLAR D53372362006 0804

170 NSA5075-6 COLLAR D53372362006 0806

194 DAN11-6X COLLAR D53372362006 0807

41 DAN11-8X COLLAR D53372362006 0810

210 NSA5076-6 COLLAR D53372362006 0816

8 DAN12-6X COLLAR D53372362006 0817

20 DAN6-6-5 PIN D53372362006 0865

8 DAN6-6-6 PIN D53372362006 0866

4 DAN5-8-7X PIN D53372362006 0887

5 DAN5-8-8X PIN D53372362006 0888

7 DAN5-8-9X PIN D53372362006 0889

10 DAN5-8-10X PIN D53372362006 0890

7 DAN5-8-11X PIN D53372362006 0891

8 DAN5-8-12X PIN D53372362006 0892

36 DAN5-5-4 PIN D53372362006 0944

16 DAN5-5-5 PIN D53372362006 0945

4 DAN5-5-9 PIN D53372362006 0949

3 DAN7-5-5 PIN D53372362006 0955

47
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

NOTE : Refer to the AIRBUS Standards Manual (SM) if you f

numbers of hardware components in the related kit(

cannot identify in the LIST OF COMPONENTS of this 

Bulletin. The SM will give you the correct part num

number relationship.

Kit 281145D06R00

10 DAN5-6-7 PIN D53372362006 0967

18 DAN5-6-8 PIN D53372362006 0968

4 DAN5-6-9 PIN D53372362006 0969

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM 

1 D5347449320000 FITTING D53470076004 0010

1 D5337217620000 PLATE D53470076004 0012

1 D5347449521600 SECTION D53470076004 0014

1 D5347658920000 FITTING D53470076004 0016

1 D5347659220000 SHIM D53470076004 0018

1 D5347659020000 FITTING D53470076004 0020

6 D5347470020200 ANGLE D53470076004 0022

1 D5347470020300 ANGLE D53470076004 0023

3 D5347470020400 ANGLE D53470076004 0024

1 D5347449520400 SECTION D53470076004 0026

3 D5347449520500 SECTION D53470076004 0027

3 D5347449520300 SECTION D53470076004 0028

1 D5347470021400 ANGLE D53470076004 0030

1 D5337217620800 FILLER D53470076004 0032

1 D5347470023200 ANGLE D53470076004 0034

1 D5347470023400 ANGLE D53470076004 0036

2 D5337217620400 SHIM D53470076004 0038

1 D5347470520000 ANGLE D53470076004 0040

1 D5347470520100 ANGLE D53470076004 0041

1 D5347470021000 ANGLE D53470076004 0042

1 D5347470021200 ANGLE D53470076004 0044

1 D5347470024000 ANGLE D53470076004 0046

1 D5347658220200 SHIM D53470076004 0048

1 D5347470023800 ANGLE D53470076004 0050

1 D5347470023600 ANGLE D53470076004 0052

1 D5347659320000 FITTING D53470076004 0054

48
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

1 D5347470520300 SUPPORT D53470076004 0066

1 D5347657820000 WEB D53470076004 0068

1 D5347658820000 WEB D53470076004 0070

1 D5347470025000 ANGLE D53470076004 0072

1 D5347470025200 ANGLE D53470076004 0074

1 D5347657920000 WEB D53470076004 0076

1 D5347449522600 SECTION D53470076004 0078

1 D5347449522800 SECTION D53470076004 0080

1 D5347550021000 KEY D53470076004 0082

1 D5347471320800 PLATE D53470076004 0084

1 D5347471321000 PLATE D53470076004 0086

1 D5347449522000 SECTION D53470076004 0088

1 D5347449522200 SECTION D53470076004 0090

1 D5347449522400 SECTION D53470076004 0092

1 D5347449523800 SECTION D53470076004 0094

1 D5347449523400 SECTION D53470076004 0096

2 D5347449524000 SECTION D53470076004 0098

1 D5347449524200 SECTION D53470076004 0100

1 D5347471321800 PLATE D53470076004 0102

1 D5347470520500 SUPPORT D53470076004 0104

1 D5347044922600 SHIM D53470076004 0106

3 D5347044922800 SHIM D53470076004 0108

1 D5337217625800 PLATE D53470076004 0110

1 D5347044924200 SHIM D53470076004 0150

1 D5347646320400 DOUBLER D53470076004 0160

1 D5347646321000 DOUBLER D53470076004 0162

1 D5347470920200 COVER D53470076004 0164

2 D5347669200000 PLATE D53470076004 0166

2 D5347669000000 TUBE D53470076004 0172

2 D5347669100000 PLUG D53470076004 0174

2 D5347472120200 SHIM D53470076004 0176

4 D5347470220000 SHIM D53470076004 0178

2 D5347472120400 SHIM D53470076004 0180

1 D5347660220200 SHIM D53470076004 0182

3 D5347449420600 FITTING D53470076004 0200

1 D5347449421100 FITTING D53470076004 0201

2 D5347448420200 STRAP D53470076004 0202

1 D5347448420300 STRAP D53470076004 0203

49
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

1 D5347065620400 SECTION D53470076004 0242

1 D5347449820400 FITTING D53470076004 0244

8 NAS1791A3-1 NUT D53470076004 0260

2 MS16625-4212 RING D53470076004 0500

10 NAS1153E7 SCREW D53470076004 0502

8 ABS0337-01A RECEPTCL D53470076004 0504

2 NAS1096-3-10 SCREW D53470076004 0506

10 NAS1474A3 NUT D53470076004 0510

16 MBBN4477-4010 RIVET D53470076004 0541

294 MBBN4477-4810 RIVET D53470076004 0549

106 LN9198-4010CF RIVET D53470076004 0640

290 LN9198-4810CF RIVET D53470076004 0648

6 LN9198-6410CF RIVET D53470076004 0664

4 DAN6-6-5X PIN D53470076004 0665

7 DAN6-6-6X PIN D53470076004 0666

25 DAN6-6-7X PIN D53470076004 0667

18 DAN6-6-8X PIN D53470076004 0668

8 DAN6-6-7Y PIN D53470076004 0677

8 DAN6-6-8Y PIN D53470076004 0678

44 DIN65399-2410CF RIVET D53470076004 0724

12 DAN5-6-5X PIN D53470076004 0765

18 DAN5-6-7X PIN D53470076004 0767

3 DAN5-6-8X PIN D53470076004 0768

16 NSA5330-6 COLLAR D53470076004 0803

565 NSA5075-6 COLLAR D53470076004 0806

87 DAN11-6X COLLAR D53470076004 0807

33 NSA5075-8 COLLAR D53470076004 0808

68 DAN6-6-3 PIN D53470076004 0863

8 DAN6-6-4 PIN D53470076004 0864

62 DAN6-6-5 PIN D53470076004 0865

73 DAN6-6-6 PIN D53470076004 0866

22 DAN6-6-7 PIN D53470076004 0867

54 DAN6-6-8 PIN D53470076004 0868

28 DAN6-6-10 PIN D53470076004 0870

30 DAN5-6-3 PIN D53470076004 0963

71 DAN5-6-4 PIN D53470076004 0964

81 DAN5-6-5 PIN D53470076004 0965

28 DAN5-6-6 PIN D53470076004 0966

50
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

NOTE : Refer to the AIRBUS Standards Manual (SM) if you f

numbers of hardware components in the related kit(

cannot identify in the LIST OF COMPONENTS of this 

Bulletin. The SM will give you the correct part num

number relationship.

Kit 281145D07R00

NOTE : Refer to the AIRBUS Standards Manual (SM) if you f

numbers of hardware components in the related kit(

cannot identify in the LIST OF COMPONENTS of this 

Bulletin. The SM will give you the correct part num

number relationship.

Kit 281145D08R00

NOTE : Refer to the AIRBUS Standards Manual (SM) if you f

numbers of hardware components in the related kit(

cannot identify in the LIST OF COMPONENTS of this 

Bulletin. The SM will give you the correct part num

number relationship.

12 DAN5-8-7 PIN D53470076004 0987

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM 

1 D5337270100000 ANGLE D53370780004 0030

1 D5337270100200 ANGLE D53370780004 0032

1 D5337270100400 ANGLE D53370780004 0034

1 D5337270100600 ANGLE D53370780004 0036

1 D5337270100800 ANGLE D53370780004 0038

1 D5337270101000 ANGLE D53370780004 0040

8 ASNA0082-203 BOLT D53370780004 0263

4 ASNA0082-204 BOLT D53370780004 0264

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM 

102 NSA5075-6 COLLAR D53470096002 0806

12 DAN6-6-3 PIN D53470096002 0863

12 DAN6-6-5 PIN D53470096002 0865

54 DAN5-6-3 PIN D53470096002 0963

24 DAN5-6-4 PIN D53470096002 0964

51
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

Kit 281145D11R00

NOTE : Refer to the AIRBUS Standards Manual (SM) if you f

numbers of hardware components in the related kit(

cannot identify in the LIST OF COMPONENTS of this 

Bulletin. The SM will give you the correct part num

number relationship.

Kit 281145D13R01

1 D2587085305600 BLANKET D25870003048 0003

1 D2587085405200 BLANKET D25870003048 0004

1 D2587085505400 BLANKET D25870003048 0005

1 D2587085602200 BLANKET D25870003048 0006

1 D2587085705200 BLANKET D25870003048 0007

1 D2587085805200 BLANKET D25870003048 0008

1 D2587085905200 BLANKET D25870003048 0009

1 D2587086005400 BLANKET D25870003048 0010

1 D2587086105200 BLANKET D25870003048 0011

1 D2587086202200 BLANKET D25870003048 0012

1 D2587086302400 BLANKET D25870003048 0013

1 D2587086502200 BLANKET D25870003048 0014

1 D2587087102200 BLANKET D25870003048 0015

1 D2587087302200 BLANKET D25870003048 0016

80 F2587003400000 STRIP D25870003048 0100

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM 

1 D9357040100200 BRACKET D93070668000 0112

1 D9357040100300 BRACKET D93070668000 0113

4 NAS1919B04-02 RIVET D93070668000 0125

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM 

1 D2827093320400 FLANGE D28270972002 0000

1 D2827093100200 TUBE D28270972002 0002

1 D2827093000200 TUBE D28270972002 0004

1 D2827093321400 SLEEVE D28270972002 0006

1 D2827093100000 TUBE D28270972002 0008

1 D2827093000000 TUBE D28270972002 0010

1 D2827093221200 SPACER D28270972002 0012

52
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

1 D2827093320600 FLANGE D28270972002 0030

2 A2827090120400 SPACER D28270972002 0031

1 D2827092900600 TUBE D28270972002 0032

1 D2827093500000 BRACKET D28270972002 0033

1 D2827092800400 TUBE D28270972002 0034

1 D2827093500200 CLAMP D28270972002 0035

2 D2827093321200 SLEEVE D28270972002 0036

1 D2827093500400 CLAMP D28270972002 0037

2 D2827093320800 FLANGE D28270972002 0038

1 D2827093322200 SLEEVE D28270972002 0039

2 D2827093221600 FLANGE D28270972002 0040

2 D2827093321000 SLEEVE D28270972002 0042

1 D2827092800000 TUBE D28270972002 0044

1 D2827092900000 TUBE D28270972002 0046

1 D2827092900200 TUBE D28270972002 0048

1 D2827092900400 TUBE D28270972002 0050

1 D2827094800000 BRACKET D28270972002 0051

1 D2827092800200 TUBE D28270972002 0052

4 NSA8203-151 ORING D28270972002 0053

9 NSA8203-152 ORING D28270972002 0054

1 NSA8203-154 ORING D28270972002 0055

1 NSA8203-156 ORING D28270972002 0056

3 NSA8203-222 ORING D28270972002 0057

9 NSA8203-226 ORING D28270972002 0058

3 NSA8203-230 ORING D28270972002 0059

10 NSA8203-234 ORING D28270972002 0060

4 NSA5519-25 CLAMP D28270972002 0061

4 NSA5519-30 CLAMP D28270972002 0062

2 ABS0107-150 NUT D28270972002 0064

3 NSA840003-150 RING D28270972002 0065

7 ABS0107-200 NUT D28270972002 0066

7 NSA840003-200 RING D28270972002 0067

2 AN814-4DL PLXBLDR D28270972002 0071

2 NSA8200-4 PACKING D28270972002 0072

3 A2827090220200 SPRING D28270972002 0074

6 A2827051720200 SPRING D28270972002 0075

63 NAS1149C0432R WASHER D28270972002 0082

52 NAS1149C0332R WASHER D28270972002 0083

53
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

NOTE : Refer to the AIRBUS Standards Manual (SM) if you f

numbers of hardware components in the related kit(

cannot identify in the LIST OF COMPONENTS of this 

Bulletin. The SM will give you the correct part num

number relationship.

Kit 281145D14R00

6 NAS1304-8 BOLT D28270972002 0089

4 NAS1304-9 BOLT D28270972002 0090

11 NAS1304-10 BOLT D28270972002 0091

9 NAS1304-11 BOLT D28270972002 0092

4 NAS1304-12 BOLT D28270972002 0093

8 NAS1304-14 BOLT D28270972002 0094

2 NAS1303-2 BOLT D28270972002 0095

21 NAS1303-3 BOLT D28270972002 0096

8 NAS1304-2 BOLT D28270972002 0098

4 NAS1304-3 BOLT D28270972002 0100

4 E0089-10-125NN LEAD D28270972002 0102

1 E0089-10-160NN LEAD D28270972002 0103

2 E0089-10-200NN LEAD D28270972002 0104

4 E0089-41-100NN LEAD D28270972002 0105

2 E0089-41-200NN LEAD D28270972002 0106

2 E0089-41-280NN LEAD D28270972002 0107

3 E0088-10-125 LEAD D28270972002 0108

2 E0088-10-200 LEAD D28270972002 0109

0.34

5

ME NSA937210MB0300 TUBING D28270972002 0110

0.38 ME NSA937210MB0300 TUBING D28270972002 0111

2 E0089-10-250NN LEAD D28270972002 0112

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM 

2 MS21902D8 UNION D28270973002 0000

2 NSA8200-8 PACKING D28270973002 0001

1 MS21907D8 ELBOW D28270973002 0002

2 AN924-8D NUT D28270973002 0003

2 NAS1149D1290K WASHER D28270973002 0004

2 MS21905D8 TEE D28270973002 0005

1 NSA5527-03-16 SPACER D28270973002 0006

54
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

2 NAS1096-3-10 SCREW D28270973002 0012

1 MS21912D8 TEE D28270973002 0013

9 MS21919WDE8 CLAMP D28270973002 0014

6 MS21919WDE11 CLAMP D28270973002 0015

1 MS21919WDE48 CLAMP D28270973002 0016

1 MS21916D8-6 REDUCER D28270973002 0017

3 NAS1149C0432R WASHER D28270973002 0018

3 NAS1304-4 BOLT D28270973002 0019

1 NSA8200-6 PACKING D28270973002 0022

2 NAS1149D1216H WASHER D28270973002 0023

3 NAS1096-3-9 SCREW D28270973002 0024

6 E0090-10-125NN LEAD D28270973002 0025

1 NAS1149D0316H WASHER D28270973002 0026

1 NAS1303-2 BOLT D28270973002 0027

1 NSA5575-7 CLAMP D28270973002 0028

4 NAS1304-2 BOLT D28270973002 0030

4 NAS1726-4E NUT D28270973002 0032

1 NAS1763D080808 TEE D28270973002 0033

12 NSA5519-11 CLAMP D28270973002 0035

12 NAS1291C3M NUT D28270973002 0036

1 E0090-10-200NN LEAD D28270973002 0037

2 E0091-10-280NN LEAD D28270973002 0038

1 D56KAN002 HOSE D28270973002 0039

2 ASNA0033-016 CLAMP D28270973002 0040

1 D2827093603400 TUBE D28270973002 0100

1 D2827093600200 TUBE D28270973002 0102

1 D2827093603200 TUBE D28270973002 0108

1 D2827093601600 TUBE D28270973002 0116

1 D2827093602000 TUBE D28270973002 0120

1 D2827093602400 TUBE D28270973002 0124

1 D2827093602600 TUBE D28270973002 0126

1 D2827093603000 TUBE D28270973002 0130

1 D2827097600200 TUBE D28270973002 0134

1 D2827093603600 TUBE D28270973002 0136

1 D2827097600400 TUBE D28270973002 0138

1 51263408-0840 HOSE D28270973002 0202

1 D2827094320000 FITTING D28270973002 0204

1 L83A13-617 MONITOR D28270973002 0206

55
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

NOTE : Refer to the AIRBUS Standards Manual (SM) if you f

numbers of hardware components in the related kit(

cannot identify in the LIST OF COMPONENTS of this 

Bulletin. The SM will give you the correct part num

number relationship.

Kit 281145D15R00

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM 

5 MS21919WDE8 CLAMP D28270974002 0014

15 NAS1096-3-8 SCREW D28270974002 0016

16 NAS1149C0332R WASHER D28270974002 0017

2 MS21905D8 TEE D28270974002 0021

1 NSA855120-8D ELBOW D28270974002 0022

1 NAS1762D0808 ELBOW D28270974002 0023

1 MS21916D8-6 REDUCER D28270974002 0025

1 NSA8200-6 PACKING D28270974002 0026

3 NAS1149C0432R WASHER D28270974002 0027

3 NAS1304-4 BOLT D28270974002 0028

2 MS21914-8D CAP D28270974002 0033

1 AN924-8D NUT D28270974002 0034

1 NAS1149D1290K WASHER D28270974002 0035

1 MS21912D8 TEE D28270974002 0036

1 NAS1149D1216H WASHER D28270974002 0037

10 NAS1291C3M NUT D28270974002 0049

9 NSA5519-11 CLAMP D28270974002 0051

2 ASNA0033-016 CLAMP D28270974002 0056

1 D56KAN002 HOSE D28270974002 0057

1 E0090-10-125NN LEAD D28270974002 0060

5 E0090-10-160NN LEAD D28270974002 0061

1 D2827097700200 TUBE D28270974002 0122

1 D2827097700400 TUBE D28270974002 0124

1 D2827093701800 TUBE D28270974002 0130

1 D2827097701000 TUBE D28270974002 0132

1 D2827097701200 TUBE D28270974002 0134

1 L83A13-617 MONITOR D28270974002 0202

1 513535E0107-090 HOSE D28270974002 0204

1 D2827094421600 PLACARD D28270974002 0216

56
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM 

1 D2827098000800 TUBE D28270975004 0005

1 D2827098001400 TUBE D28270975004 0011

1 D2827097901200 TUBE D28270975004 0013

1 D2827097901400 TUBE D28270975004 0015

1 D2827097901000 TUBE D28270975004 0016

1 D2827097901600 TUBE D28270975004 0017

1 D2827097901800 TUBE D28270975004 0019

1 D2827097902000 TUBE D28270975004 0021

1 D2827097902400 TUBE D28270975004 0025

1 D2827097904000 TUBE D28270975004 0026

1 A2163302000000 FILTER D28270975004 0027

1 A2151034520000 INLET D28270975004 0028

1 MS21902D10 UNION D28270975004 0030

1 NAS1612-10 PACKING D28270975004 0031

1 83694912 HOSE D28270975004 0040 

2 A2827092300000 COUPLING D28270975004 0050

27 NAS1726C3E NUT D28270975004 0070

18 NAS1096-3-8 SCREW D28270975004 0071

27 NAS1149C0332R WASHER D28270975004 0073

2 AN924-10J NUT D28270975004 0074

2 MS21909J10 TEE D28270975004 0075

2 NAS1149F1432P WASHER D28270975004 0076

1 TSTMNR503-0 CONDUIT D28270975004 0077

4 NSA935401-03 TIE D28270975004 0078

10 MS21919WDE10 CLAMP D28270975004 0079

11 MS21919WDE4 CLAMP D28270975004 0080

8 NSA5575-8A CLAMP D28270975004 0081

3 NSA5575-2 CLAMP D28270975004 0082

7 E0090-10-125NN LEAD D28270975004 0083

4 E0090-18-100NN LEAD D28270975004 0084

4 NAS1096-1-8 SCREW D28270975004 0085

4 MS21042-06 NUT D28270975004 0087

8 NAS1303-2 BOLT D28270975004 0088

8 NAS1726-3E NUT D28270975004 0089

1 MS21908J10 ELBOW D28270975004 0091

1 AN924-4D NUT D28270975004 0092

57
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

NOTE (01) Part number supplied, 1451515F0150-180.

NOTE : Refer to the AIRBUS Standards Manual (SM) if you f

numbers of hardware components in the related kit(

cannot identify in the LIST OF COMPONENTS of this 

Bulletin. The SM will give you the correct part num

number relationship.

Kit 281145D17R00

2 NAS1096-3-12 SCREW D28270975004 0098

1 MS21905J10 TEE D28270975004 0099

1 MS21919WCH15 CLAMP D28270975004 0101

1 E0090-10-160NN LEAD D28270975004 0102

16 NAS1149F0332P WASHER D28270975004 0103

8 NAS1149FN616P WASHER D28270975004 0104

1 D2827094420000 PLACARD D28270975004 0200

1 D2827094420200 PLACARD D28270975004 0202

1 D2827094420400 PLACARD D28270975004 0204

1 D2827094420600 PLACARD D28270975004 0206

1 D2827094420800 PLACARD D28270975004 0208

1 D2827094421000 PLACARD D28270975004 0210

1 D2827094421200 PLACARD D28270975004 0212

1 D2827098002400 TUBE D28270975004 0220

1 D2827098002600 TUBE D28270975004 0222

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM 

6 NAS1096-3-8 SCREW D28270982004 0004

6 NAS1149C0332R WASHER D28270982004 0005

6 NAS1726C3E NUT D28270982004 0006

69 LN9198-3212BF RIVET D28270982004 0032

69 LN9198-4012BF RIVET D28270982004 0040

8 DAN7-6-8Y PIN D28270982004 0041

8 DAN12-6Y COLLAR D28270982004 0042

3 F5397461900600 BRACKET D28270982004 0100

2 D2827094222800 ANGLE D28270982004 0102

1 D2827098300000 BRACKET D28270982004 0104

1 D2827098300200 BRACKET D28270982004 0106

3 D2827094221400 ANGLE D28270982004 0112

58
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

NOTE : Refer to the AIRBUS Standards Manual (SM) if you f

numbers of hardware components in the related kit(

cannot identify in the LIST OF COMPONENTS of this 

Bulletin. The SM will give you the correct part num

number relationship.

Kit 281145D18R00

NOTE : Refer to the AIRBUS Standards Manual (SM) if you f

numbers of hardware components in the related kit(

cannot identify in the LIST OF COMPONENTS of this 

Bulletin. The SM will give you the correct part num

number relationship.

Kit 281145D19R00

1 D2827098321200 ANGLE D28270982004 0119

2 D2827094200400 BRACKET D28270982004 0124

1 D2827098325200 BRACKET D28270982004 0125

1 D2827098300800 BRACKET D28270982004 0126

2 D2827098323200 BRACKET D28270982004 0127

1 D2827098323000 BRACKET D28270982004 0128

1 D2827098323800 BRACKET D28270982004 0130

1 D2827093521000 BRACKET D28270982004 0131

1 D2827098324200 BRACKET D28270982004 0132

1 D2827098324400 BRACKET D28270982004 0133

1 D2827098324000 BRACKET D28270982004 0134

1 D2827098326000 BRACKET D28270982004 0135

1 D2827098326200 BRACKET D28270982004 0136

2 D2827098327600 ANGLE D28270982004 0137

1 D2827098327800 ANGLE D28270982004 0138

1 D2827098328000 ANGLE D28270982004 0139

1 D2827098328200 ANGLE D28270982004 0140

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM 

1 D2827099720000 BEAM D28270998002 0000

8 NSA5031-3-10 BOLT D28270998002 0770

8 NAS1726C3P NUT D28270998002 0807

8 NAS1149C0332R WASHER D28270998002 0808

59
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

NOTE : Refer to the AIRBUS Standards Manual (SM) if you f

numbers of hardware components in the related kit(

cannot identify in the LIST OF COMPONENTS of this 

Bulletin. The SM will give you the correct part num

number relationship.

Kit 281145D20R00

NOTE : Refer to the AIRBUS Standards Manual (SM) if you f

numbers of hardware components in the related kit(

cannot identify in the LIST OF COMPONENTS of this 

Bulletin. The SM will give you the correct part num

number relationship.

Kit 281145D25R00

Kit 281145D26R00

Kit 281145D27R00

1 D2827099600400 SHIELD D28270999004 0022

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM 

1 D2827050501600 TUBE D28270515000 0002

1 NSA855113-11C TEE D28270515000 0021

1 D2827050502600 TUBE D28270515000 0044

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM 

1 D2557131000200 PANEL D25571073000 0000

1 D2557131400600 PANEL D25571073000 0002

1 D2557131600800 PANEL D25571073000 0004

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM 

1 D2557132600200 PANEL D25571073002 0010

1 D2557132401000 PANEL D25571073002 0012

1 D2557132200600 PANEL D25571073002 0014

60
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

Kit 281145D31R00

NOTE : Refer to the AIRBUS Standards Manual (SM) if you f

numbers of hardware components in the related kit(

cannot identify in the LIST OF COMPONENTS of this 

Bulletin. The SM will give you the correct part num

number relationship.

Kit 281145D32R00

NOTE : Refer to the AIRBUS Standards Manual (SM) if you f

numbers of hardware components in the related kit(

cannot identify in the LIST OF COMPONENTS of this 

Bulletin. The SM will give you the correct part num

number relationship.

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM 

1 D2557123600400 PANEL D25571073006 0030

1 D2557123600500 PANEL D25571073006 0031

1 D2557123800200 PANEL D25571073006 0032

2 D2557017000200 COVER D25571073006 0040

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM 

1 D5367161701800 PANEL D53675015002 0016

2 D5367160001600 PANEL D53675015002 0030

1 D5367160100800 PANEL D53675015002 0032

1 D5367162400800 PANEL D53675015002 0036

1 D5367150100200 PANEL D53675015002 0040

2 D5367162301400 PANEL D53675015002 0042

1 D5367150500800 PANEL D53675015002 0044

36 ABS0376-3-23 SCREW D53675015002 0398

130 ABS0376-3-25 SCREW D53675015002 0400

166 EN6131-3C1 NUT D53675015002 0505

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM 

38.5

41

ME DAN107-1 CORD D53675016002 0385

38.5

41

ME ABS5093AT25 TAPE D53675016002 0387

61
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

NOTE : Refer to the AIRBUS Standards Manual (SM) if you f

numbers of hardware components in the related kit(

cannot identify in the LIST OF COMPONENTS of this 

Bulletin. The SM will give you the correct part num

number relationship.

Kit 281145D34R00

NOTE : Refer to the AIRBUS Standards Manual (SM) if you f

numbers of hardware components in the related kit(

cannot identify in the LIST OF COMPONENTS of this 

Bulletin. The SM will give you the correct part num

number relationship.

Kit 281145D36R00

1 D5367520802600 PANEL D53675510000 0038

1 D5367521104000 PANEL D53675510000 0084

1 D5367521104200 PANEL D53675510000 0086

1 D5367521104400 PANEL D53675510000 0088

1 D5367521104600 PANEL D53675510000 0090

1 D5367521104800 PANEL D53675510000 0092

1 D5367521105000 PANEL D53675510000 0094

1 D5397484220000 PLATE D53675510000 0110

1 D5397484220100 PLATE D53675510000 0111

2 D5397489520000 SPACER D53675510000 0118

2 D5397489520100 SPACER D53675510000 0119

61 ABS0376-3-30 SCREW D53675510000 0402

95 ABS0376-3-40 SCREW D53675510000 0404

12 NAS1102-3-8 SCREW D53675510000 0408

1 NAS1102-3-24 SCREW D53675510000 0409

80 EN6131-3C1 NUT D53675510000 0410

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM 

2.25 ME ABS0305LC SECTION D53675511000 0001

12.1 ME ABS0399A SECTION D53675511000 0004

21.0

62

ME DAN107-1 CORD D53675511000 0005

62
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

NOTE : Refer to the AIRBUS Standards Manual (SM) if you f

numbers of hardware components in the related kit(

cannot identify in the LIST OF COMPONENTS of this 

Bulletin. The SM will give you the correct part num

number relationship.

Kit 281145D40R01

1 D5397469000100 BRACKET D53975019000 0017

1 D5397469200000 BRACKET D53975019000 0018

1 D5397469200100 BRACKET D53975019000 0019

1 D5397469300000 BRACKET D53975019000 0020

1 D5397469300100 BRACKET D53975019000 0021

44 NAS6703-2 BOLT D53975019000 0025

44 NAS1149D0332K WASHER D53975019000 0026

22 D5397469700000 SUPPORT D53975019000 0028

1 D5347047400200 SECTION D53975019000 0030

1 D5347047400300 SECTION D53975019000 0031

1 D5397467800800 SECTION D53975019000 0040

1 D5397467800900 SECTION D53975019000 0041

1 D5397492600000 SECTION D53975019000 0042

1 D5397468800200 SECTION D53975019000 0044

1 D5397468800300 SECTION D53975019000 0045

1 D5397468000400 SECTION D53975019000 0046

1 D5397468000500 SECTION D53975019000 0047

1 D5397492500000 SECTION D53975019000 0048

1 D5397492500200 SECTION D53975019000 0050

1 D5397467400500 SECTION D53975019000 0052

1 D5397467400400 SECTION D53975019000 0053

3 D5397492700000 PLATE D53975019000 0054

9 NAS1102E3-7 SCREW D53975019000 0400

9 DAN125-4 WASHER D53975019000 0402

190 NAS1097AD4-12 RIVET D53975019000 0532

8 LN9198-4816CF RIVET D53975019000 0648

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM 

2 D5347035000600 XBEAM D53470075004 0010

4 D5337217620000 PLATE D53470075004 0012

3 D5337217620100 PLATE D53470075004 0014

63
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

8 D5337217620800 FILLER D53470075004 0026

4 D5347449520300 SECTION D53470075004 0028

3 D5347449520200 SECTION D53470075004 0030

7 D5347449520500 SECTION D53470075004 0032

6 D5347449520400 SECTION D53470075004 0034

1 D5347470020000 ANGLE D53470075004 0036

1 D5347470020100 ANGLE D53470075004 0038

3 D5347470020400 ANGLE D53470075004 0044

2 D5347470020500 ANGLE D53470075004 0046

6 D5347470020200 ANGLE D53470075004 0048

4 D5347470020300 ANGLE D53470075004 0050

1 D5347026000600 XBEAM D53470075004 0052

2 D5347470520000 ANGLE D53470075004 0054

2 D5347470520100 ANGLE D53470075004 0056

1 D5347449523400 SECTION D53470075004 0058

1 D5347449523600 SECTION D53470075004 0060

2 D5347449522000 SECTION D53470075004 0062

2 D5347449523200 SECTION D53470075004 0064

1 D5347470320000 WEB D53470075004 0066

1 D5347470020800 ANGLE D53470075004 0068

1 D5347470021000 ANGLE D53470075004 0070

1 D5347470020600 ANGLE D53470075004 0072

1 D5347470021200 ANGLE D53470075004 0074

1 D5347035300600 XBEAM D53470075004 0076

1 D5337217620700 PLATE D53470075004 0078

1 D5347470420400 WEB D53470075004 0080

1 D5347470021600 ANGLE D53470075004 0082

1 D5347470021800 ANGLE D53470075004 0084

1 D5347470024800 ANGLE D53470075004 0086

1 D5347470043800 ANGLE D53470075004 0088

1 D5347470021400 ANGLE D53470075004 0090

1 D5347470022200 ANGLE D53470075004 0092

1 D5347449520200 SECTION D53470075004 0094

1 D5347449520400 SECTION D53470075004 0096

1 D5347470020500 ANGLE D53470075004 0098

2 D5347470020300 ANGLE D53470075004 0100

1 D5347658420000 ANGLE D53470075004 0102

1 D5347471321200 PLATE D53470075004 0104

64
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

2 D5347471500300 PLATE D53470075004 0118

1 D5347471500100 PLATE D53470075004 0120

1 D5347471501400 PLATE D53470075004 0122

1 D5347471502600 PLATE D53470075004 0124

1 D5347659100000 ANGLE D53470075004 0126

6 D5347470120000 ANGLE D53470075004 0128

7 D5347470120200 ANGLE D53470075004 0130

4 D5347470120100 ANGLE D53470075004 0132

5 D5347470120300 ANGLE D53470075004 0134

1 D5347471322400 PLATE D53470075004 0138

1 D5347471322600 PLATE D53470075004 0140

1 D5347048100600 SECTION D53470075004 0152

1 D5347047500800 SECTION D53470075004 0154

1 D5347047600800 SECTION D53470075004 0156

1 D5347646320200 DOUBLER D53470075004 0160

1 D5347646320000 DOUBLER D53470075004 0162

1 D5347470920200 COVER D53470075004 0164

2 D5347669200000 PLATE D53470075004 0166

2 D5347669000000 TUBE D53470075004 0172

2 D5347669100000 PLUG D53470075004 0174

4 D5347472120000 SHIM D53470075004 0176

4 D5347470220000 SHIM D53470075004 0178

4 D5347658620000 BUSHING D53470075004 0204

1 D5347065020400 SECTION D53470075004 0208

1 D5347048800400 PLATE D53470075004 0214

1 D5347048900400 PLATE D53470075004 0216

1 D5347049200400 PLATE D53470075004 0218

1 D5347046824500 ANGLE D53470075004 0220

1 D5347046824300 ANGLE D53470075004 0222

1 D5347046824600 ANGLE D53470075004 0224

2 D5347046824000 ANGLE D53470075004 0228

1 D5347046823800 ANGLE D53470075004 0230

1 D5347046823600 ANGLE D53470075004 0232

1 D5347046824200 ANGLE D53470075004 0234

1 D5347046824400 ANGLE D53470075004 0236

2 MS16625-4212 RING D53470075004 0500

10 NAS1153E7 SCREW D53470075004 0502

8 ABS0337-01A RECEPTCL D53470075004 0504

65
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

NOTE : Refer to the AIRBUS Standards Manual (SM) if you f

numbers of hardware components in the related kit(

cannot identify in the LIST OF COMPONENTS of this 

969 LN9198-4010CF RIVET D53470075004 0640

548 LN9198-4810CF RIVET D53470075004 0648

4 DAN6-6-5X PIN D53470075004 0665

3 DAN6-6-6X PIN D53470075004 0666

11 DAN6-6-7X PIN D53470075004 0667

10 DAN6-6-9X PIN D53470075004 0669

8 DAN6-6-8Y PIN D53470075004 0678

36 DIN65399-2410CF RIVET D53470075004 0724

84 DIN65399-3210CF RIVET D53470075004 0732

10 DAN5-6-4X PIN D53470075004 0764

24 DAN5-6-5X PIN D53470075004 0765

8 DAN5-6-6X PIN D53470075004 0766

14 DAN5-6-8X PIN D53470075004 0768

8 DAN5-6-8Y PIN D53470075004 0778

16 NSA5330-6 COLLAR D53470075004 0803

3 NSA5075-5 COLLAR D53470075004 0804

749 NSA5075-6 COLLAR D53470075004 0806

69 DAN11-6X COLLAR D53470075004 0807

40 NSA5075-8 COLLAR D53470075004 0808

16 DAN6-6-3 PIN D53470075004 0863

8 DAN6-6-4 PIN D53470075004 0864

34 DAN6-6-5 PIN D53470075004 0865

4 DAN6-6-6 PIN D53470075004 0866

10 DAN6-6-7 PIN D53470075004 0867

3 DAN5-5-5 PIN D53470075004 0945

70 DAN5-6-3 PIN D53470075004 0963

183 DAN5-6-4 PIN D53470075004 0964

187 DAN5-6-5 PIN D53470075004 0965

126 DAN5-6-6 PIN D53470075004 0966

40 DAN5-6-7 PIN D53470075004 0967

81 DAN5-6-8 PIN D53470075004 0968

20 DAN5-6-10 PIN D53470075004 0970

24 DAN5-8-5 PIN D53470075004 0985

8 DAN5-8-6 PIN D53470075004 0986

8 DAN5-8-7 PIN D53470075004 0987

66
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

NOTE : Refer to the AIRBUS Standards Manual (SM) if you f

numbers of hardware components in the related kit(

cannot identify in the LIST OF COMPONENTS of this 

Bulletin. The SM will give you the correct part num

number relationship.

Kit 281145D42R03

16 DAN6-6-3 PIN D53470095002 0863

16 DAN6-6-5 PIN D53470095002 0865

72 DAN5-6-3 PIN D53470095002 0963

32 DAN5-6-4 PIN D53470095002 0964

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM 

1 D2557258500800 TRACK D25572585012 0007

1 D2557268121000 DOUBLER D25572585012 0009

1 D2557268028600 PLATE D25572585012 0010

1 D2557258501000 TRACK D25572585012 0011

1 D2557265025800 PLATE D25572585012 0012

2 D2557237320600 BOLT D25572585012 0013

3 NAS1149C0563R WASHER D25572585012 0014

2 MS24665-300 PIN D25572585012 0015

14 MS21042-3 NUT D25572585012 0016

14 NAS1153-3 SCREW D25572585012 0017

1 D2557224601000 TRACK D25572585012 0018

1 D2557224600600 TRACK D25572585012 0019

56 NAS1102-3-7 SCREW D25572585012 0026

166 NAS1102-3-10 SCREW D25572585012 0027

436 NAS1726-3E NUT D25572585012 0028

38 NAS1100-3-12 SCREW D25572585012 0029

19 NAS1100-3-14 SCREW D25572585012 0030

25 MS21250-03008 BOLT D25572585012 0031

52 NAS1102-3-9 SCREW D25572585012 0032

16 NAS1133E5 SCREW D25572585012 0033 

108 MS21250-03010 BOLT D25572585012 0034

4 MS21250-03012 BOLT D25572585012 0035

6 NSA5042C05-180 BOLT D25572585012 0036

6 NSA5060-4 NUT D25572585012 0037

67
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

36 DAN12-5 COLLAR D25572585012 0043

42 NAS1102-3-8 SCREW D25572585012 0044

34 NAS1100-3-10 SCREW D25572585012 0045

10 NAS1100-3-8 SCREW D25572585012 0046

2 NSA5059-5 NUT D25572585012 0047

52 NAS1133E3 SCREW D25572585012 0048

160 MS21250-03006 BOLT D25572585012 0049

68 NAS1102-3-11 SCREW D25572585012 0050

74 NAS1102-3-12 SCREW D25572585012 0051

32 NAS1102-3-14 SCREW D25572585012 0052

35 NAS1100-3-9 SCREW D25572585012 0053

135 NAS1100-3-11 SCREW D25572585012 0054

5 NAS1100-3-6 SCREW D25572585012 0055

5 NAS1149C0332R WASHER D25572585012 0056

170 NAS1100-3-7 SCREW D25572585012 0057

18 NAS1303-7 BOLT D25572585012 0058

2 NAS1303-9 BOLT D25572585012 0059

6 D2557268030600 SHIM D25572585012 0069

6 D2557226520400 SUPPORT D25572585012 0070

6 D2557226120200 BLOCK D25572585012 0071

48 MS21250-03014 BOLT D25572585012 0072

12 D2557238000400 LATCH D25572585012 0078

18 NAS1153-13 SCREW D25572585012 0079

1 D2557240102200 SUPPORT D25572585012 0080

5 D2557268122200 PLATE D25572585012 0081

1 D2557268122400 PLATE D25572585012 0082

2 MS21250-04012 BOLT D25572585012 0083

2 MS21250-04024 BOLT D25572585012 0084

3 MS21250-04026 BOLT D25572585012 0085

4 MS21250-04030 BOLT D25572585012 0086

10 NAS1726-4E NUT D25572585012 0087

11 NAS1149F0432P WASHER D25572585012 0088

2 NAS1102-08-10 SCREW D25572585012 0091

2 NAS1726-05E NUT D25572585012 0092

1 D2557240021400 STOP D25572585012 0094

3 MS21250-06018 BOLT D25572585012 0095

3 NSA5379-6C WASHER D25572585012 0096

1 NAS1304-18 BOLT D25572585012 0097

68
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

NOTE (01) Alternative for Item 0048.

NOTE : Refer to the AIRBUS Standards Manual (SM) if you f

numbers of hardware components in the related kit(

cannot identify in the LIST OF COMPONENTS of this 

Bulletin. The SM will give you the correct part num

number relationship.

Kit 281145D43R00

NOTE : Refer to the AIRBUS Standards Manual (SM) if you f

numbers of hardware components in the related kit(

cannot identify in the LIST OF COMPONENTS of this 

Bulletin. The SM will give you the correct part num

number relationship.

Kit 281145D44R01

5 D2557268124000 PLATE D25572585012 0104

5 D2557268124200 PLATE D25572585012 0105

5 D2557268124400 PLATE D25572585012 0106

5 D2557268124600 PLATE D25572585012 0107

5 D2557268124800 PLATE D25572585012 0108

5 D2557268125000 PLATE D25572585012 0109

1 D2557224601400 TRACK D25572585012 0114

18 NAS1153-11 SCREW D25572585012 0162

18 NAS1153-15 SCREW D25572585012 0164

24 NAS1133E10 SCREW D25572585012 0165 

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM 

2 NAS1149C0332R WASHER D25572585014 0031

11 NAS1726C3P NUT D25572585014 0036

1 NSA5039-3-1 SCREW D25572585014 0042

4 NSA5030-3-2 SCREW D25572585014 0044

2 NSA5039-3-3 SCREW D25572585014 0045

2 NSA5039-3-7 SCREW D25572585014 0046

2 NSA5030-3-9 SCREW D25572585014 0047

69
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

6 D2557214633600 SHIM D25572585016 0036

40 D2557214635000 SHIM D25572585016 0050

40 D2557214635100 SHIM D25572585016 0051

40 D2557214635200 SHIM D25572585016 0052

2 D2557214635400 SHIM D25572585016 0054

2 D2557214635500 SHIM D25572585016 0055

2 D2557214635600 SHIM D25572585016 0056

2 D2557214635800 SHIM D25572585016 0058

6 D2557214636000 SHIM D25572585016 0060

6 D2557214636800 SHIM D25572585016 0066

6 D2557214637000 SHIM D25572585016 0068

12 D2557214637200 SHIM D25572585016 0070

12 D2557214637400 SHIM D25572585016 0072

4 D2557214637600 SHIM D25572585016 0076

4 D2557214637700 SHIM D25572585016 0077

4 D2557214637800 SHIM D25572585016 0078

12 D2557214638000 SHIM D25572585016 0080

12 D2557214638100 SHIM D25572585016 0081

12 D2557214638200 SHIM D25572585016 0082

2 D2557214638400 SHIM D25572585016 0084

2 D2557214638500 SHIM D25572585016 0085

2 D2557214638600 SHIM D25572585016 0086

12 D2557214638800 SHIM D25572585016 0088

12 D2557214638900 SHIM D25572585016 0089

12 D2557214639000 SHIM D25572585016 0090

6 D2557214639600 SHIM D25572585016 0096

6 D2557214639700 SHIM D25572585016 0097

6 D2557214639800 SHIM D25572585016 0098

12 D2557214640000 SHIM D25572585016 0100

12 D2557214640200 SHIM D25572585016 0102

3 D2557206229800 PLUG D25572585016 0104

2 D2557214642000 SHIM D25572585016 0106

2 D2557214642100 SHIM D25572585016 0107

2 D2557214642200 SHIM D25572585016 0108

2 D2557214642400 SHIM D25572585016 0110

2 D2557214642600 SHIM D25572585016 0112

2 D2557214642800 SHIM D25572585016 0114

2 D2557214643000 SHIM D25572585016 0116

70
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

Kit 281145D46R00

NOTE : Refer to the AIRBUS Standards Manual (SM) if you f

numbers of hardware components in the related kit(

cannot identify in the LIST OF COMPONENTS of this 

Bulletin. The SM will give you the correct part num

number relationship.

Kit 281145D47R01

2 D2557214643800 SHIM D25572585016 0128

6 NAS1102-3-10 SCREW D25572585016 0134

4 D2557214653000 SHIM D25572585016 0229

2 D2557214653800 SHIM D25572585016 0233

2 D2557214653900 SHIM D25572585016 0234

2 D2557214654000 SHIM D25572585016 0235

20 D2557214653200 SHIM D25572585016 0236

3 D2557214633800 SHIM D25572585016 0238

2 D2557214634000 SHIM D25572585016 0240

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM 

2 DAN152-1 TDP D25572585022 0009

6 NAS1102-3-10 SCREW D25572585022 0010

3 NAS1102-3-14 SCREW D25572585022 0011

9 NAS1726-3E NUT D25572585022 0013

1 D2557206230400 FITTING D25572585022 0029

1 D2557206230600 FITTING D25572585022 0031

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM 

1 D2557213623800 SHEET D25572585024 0007

2 NAS1153-27 SCREW D25572585024 0010

2 NAS1153-25 SCREW D25572585024 0014

4 NSA5039-3-6 SCREW D25572585024 0031

4 NSA5039-3-8 SCREW D25572585024 0032

11 NSA5030-3-5 SCREW D25572585024 0034

8 NAS1726-3E NUT D25572585024 0035

23 ABS0365-3-2B NUT D25572585024 0037

1 D2557214429600 SHEET D25572585024 0066

1 D2557215901800 MAT D25572585024 0070

71
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

NOTE : Refer to the AIRBUS Standards Manual (SM) if you f

numbers of hardware components in the related kit(

cannot identify in the LIST OF COMPONENTS of this 

Bulletin. The SM will give you the correct part num

number relationship.

Kit 281145D48R00

NOTE : Refer to the AIRBUS Standards Manual (SM) if you f

numbers of hardware components in the related kit(

cannot identify in the LIST OF COMPONENTS of this 

Bulletin. The SM will give you the correct part num

number relationship.

Kit 281145D49R01

NOTE : Refer to the AIRBUS Standards Manual (SM) if you f

numbers of hardware components in the related kit(

cannot identify in the LIST OF COMPONENTS of this 

Bulletin. The SM will give you the correct part num

number relationship.

Kit 281145D50R00

1.3 ME ABS5006-4B TAPE D25572585024 0077

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM 

2 NSA935401-04 TIE D25572585026 0003

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM 

1 134100-5 LATCH D25572585028 0141

1 D2557237422800 TRACK D25572585028 0142

3 D2557237423000 TRACK D25572585028 0143

4 MS21250-05028 BOLT D25572585028 0144

2 MS21250-05022 BOLT D25572585028 0145

6 MS21042-5 NUT D25572585028 0146

6 D2557238721000 SPACER D25572585028 0147

12 D2557231520400 SPACER D25572585028 0148

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM 

2 109100-1 LATCH D25572585030 0100

72
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

Kit 281145D52R00

Kit 281145D61R00

1 D2557295028100 PLACARD D25572585032 0006

4 D2557295024000 STRIP D25572585032 0008

11 D2557295024300 STRIP D25572585032 0022

1 A2557146821200 PLACARD D25572585032 0024

2 D2557295122600 PLACARD D25572585032 0030

1 D2557295123600 PLACARD D25572585032 0034

1 D2557295123800 PLACARD D25572585032 0035

2 D2557295236800 PLACARD D25572585032 0036

2 A2557144422600 PLACARD D25572585032 0038

7 D2557295030600 FOIL D25572585032 0040

1 A2557332320000 PLACARD D25572585032 0041

1 A2557332420000 PLACARD D25572585032 0042

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM 

1 AC40-0209900 NET D25572585034 0005

1 AC40-0253615 NET D25572585034 0008

1 AC40-0253610 NET D25572585034 0009

1 HA70-0214005 STANCHIN D25572585034 0011

1 AC40-0253620 NET D25572585034 0012

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM 

2 A9249175120000 ANGLE D53371046000 0001

1 D5337312600000 PLATE D53371046000 0002

1 D5337312000000 PLATE D53371046000 0003

4 D5337312420000 STRAP D53371046000 0004

8 NAS6703U7 BOLT D53371046000 0005

8 NAS6703U5 BOLT D53371046000 0006

16 NAS1726C3P NUT D53371046000 0007

16 NAS1149C0332R WASHER D53371046000 0008

1 D5337107420200 PLATE D53371046000 0009

1 D5337311520200 WALL D53371046000 0010

1 D5337311920200 PLATE D53371046000 0011

2 D5337309820000 SHEET D53371046000 0012

2 D5337307220100 STIFFENR D53371046000 0013

73
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

NOTE : Refer to the AIRBUS Standards Manual (SM) if you f

numbers of hardware components in the related kit(

cannot identify in the LIST OF COMPONENTS of this 

Bulletin. The SM will give you the correct part num

number relationship.

Kit 281145D62R00

NOTE : Refer to the AIRBUS Standards Manual (SM) if you f

numbers of hardware components in the related kit(

cannot identify in the LIST OF COMPONENTS of this 

1 D5337313420000 SECTION D53371046000 0019

3 DAN7-5A5 PIN D53371046000 0020

2 DAN6-6-4 PIN D53371046000 0021

4 DAN5-6-4 PIN D53371046000 0022

20 DAN5-6-6 PIN D53371046000 0023

4 DAN5-6-7 PIN D53371046000 0024

6 NSA5075-6 COLLAR D53371046000 0025

3 ABS0258-5C COLLAR D53371046000 0026

24 NSA5076-6 COLLAR D53371046000 0027

12 LN9198-3208BF RIVET D53371046000 0028

196 LN9198-4812CF RIVET D53371046000 0029

8 LN9198-4814CF RIVET D53371046000 0030

15 LN9198-4009CF RIVET D53371046000 0031

3 LN9198-4010CF RIVET D53371046000 0032

11 LN9198-4011CF RIVET D53371046000 0033

8 LN9198-4012CF RIVET D53371046000 0035

10 DAN5-5-7 PIN D53371046000 0036

8 DAN5-5-6 PIN D53371046000 0037

12 NSA5075-5 COLLAR D53371046000 0038

6 NSA5076-5 COLLAR D53371046000 0039

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM 

20 DAN7-6-8X PIN D53371237000 0001

32 DAN7-8-8X PIN D53371237000 0002

12 DAN7-8-10X PIN D53371237000 0003

1 DAN8-8-8X PIN D53371237000 0004

20 DAN12-6X COLLAR D53371237000 0005

45 DAN12-8X COLLAR D53371237000 0006

74
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

NOTE : Refer to the AIRBUS Standards Manual (SM) if you f

numbers of hardware components in the related kit(

cannot identify in the LIST OF COMPONENTS of this 

Bulletin. The SM will give you the correct part num

number relationship.

Kit 281145D70R00

NOTE : Refer to the AIRBUS Standards Manual (SM) if you f

numbers of hardware components in the related kit(

cannot identify in the LIST OF COMPONENTS of this 

Bulletin. The SM will give you the correct part num

number relationship.

Kit 281145D72R00

Kit 281145D73R00

32 DAN7-8-8X PIN D53371237001 0002

12 DAN7-8-10X PIN D53371237001 0003

1 DAN8-8-8X PIN D53371237001 0004

20 DAN12-6X COLLAR D53371237001 0005

45 DAN12-8X COLLAR D53371237001 0006

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM 

50 D9239310904800 PLACARD D92894713062 0000

100 NSA935401-03 TIE D92894713062 0080

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM 

2 D2527719940600 PLACARD D25288767000 0206

2 D2527700844200 PLACARD D25288767000 0242

2 A2528131544600 PLACARD D25288767000 0246

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM 

4 NAS1096-2-12 SCREW D92894736004 0007

2 NAS1096-3-9 SCREW D92894736004 0030

1 D9299043900000 HARNESS D92894736004 0039

1 D9299044000000 HARNESS D92894736004 0040

1 D9239386503200 PLCRDSET D92894736004 0050

75
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

NOTE : Refer to the AIRBUS Standards Manual (SM) if you f

numbers of hardware components in the related kit(

cannot identify in the LIST OF COMPONENTS of this 

Bulletin. The SM will give you the correct part num

number relationship.

Kit 281145D74R00

3 NSA5066-08-1 NUT D92894736004 0230

2 E0343-01 MOUNT D92894736004 0250

1 NSA935504-01 MOUNT D92894736004 0251

1 NSA935504-03 MOUNT D92894736004 0253

1 NSA935513-07 MOUNT D92894736004 0259

2 ABS0355-01 BRACKET D92894736004 0262

2 ABS0355-02 BRACKET D92894736004 0263

2 NSA935514-03 WASHER D92894736004 0264

4 NSA5527-03-03 SPACER D92894736004 0304

15 NSA935401-03 TIE D92894736004 0793

30 NSA935401-04 TIE D92894736004 0794

15 NSA935401-05 TIE D92894736004 0795

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM 

2 D2567072701000 BRACKET D25670762000 0000

6 D2567072700200 BRACKET D25670762000 0002

2 D2567072700400 BRACKET D25670762000 0004

2 D2567072700500 BRACKET D25670762000 0005

2 D2567072701200 BRACKET D25670762000 0006

3 D2567072700800 BRACKET D25670762000 0008

3 D2567072700900 BRACKET D25670762000 0009

66 LN9198-4010CF RIVET D25670762000 0100

1 D2567070100000 TUBE D25671745000 0000

1 D2567070100100 TUBE D25671745000 0001

1 D2567070100200 TUBE D25671745000 0002

1 D2567070100300 TUBE D25671745000 0003

1 D2567070600000 SECTION D25671745000 0010

1 D2567070600200 SECTION D25671745000 0012

4 E0088-10-80NN LEAD D25671745000 0050

4 ABS0396C08JA CLAMP D25671745000 0060

10 NSA5515-8 CLAMP D25671745000 0062

76
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

NOTE : Refer to the AIRBUS Standards Manual (SM) if you f

numbers of hardware components in the related kit(

cannot identify in the LIST OF COMPONENTS of this 

Bulletin. The SM will give you the correct part num

number relationship.

Kit 281145D75R00

4 NAS1096-2-7 SCREW D25671745000 0084

5 MS21042-08 NUT D25671745000 0092

2 NAS1096-3-12 SCREW D25671745000 0103

30 NAS1149D0363K WASHER D25671745000 0110

13 NAS1149DN832K WASHER D25671745000 0112

1 64079-3 HOSE D25671745000 0595

1 64079-1 HOSE D25671745000 0596

2 64079-5 HOSE D25671745000 0597

2 D2567043200000 POCKET D25671746000 0050

2 ASNA0033-172 CLAMP D25671746000 0060

1 LN29837A1 SECTION D25671746000 0070

4 NAS1096-3-7 SCREW D25671746000 0080

4 NAS1149D0363K WASHER D25671746000 0090

1 D9239310903000 PLCRDSET D25671746000 0100

2 MS20392-2C15 PIN D25671746000 0110

6 NAS1149C0332R WASHER D25671746000 0120

2 MS24665-1013 PIN D25671746000 0130

1 D2567074100600 PLACARD D25671746000 0140

1 60592-103 RESERVOR D25671746000 0594

1 60592-103 RESERVOR D25671746000 0598

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM 

16 NAS1102-4-16 SCREW D25286364014 0002

16 NAS1149F0432P WASHER D25286364014 0004

16 NAS1169C416L WASHER D25286364014 0006

16 MS21042-4 NUT D25286364014 0008

16 NAS1102-08-16 SCREW D25286364014 0010

16 NAS1149FN816P WASHER D25286364014 0012

16 NAS1169C8L WASHER D25286364014 0014

16 MS21042-08 NUT D25286364014 0016

1 FACC79120418 CMPRTMNT D25286364014 0020

77
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

NOTE : Refer to the AIRBUS Standards Manual (SM) if you f

numbers of hardware components in the related kit(

cannot identify in the LIST OF COMPONENTS of this 

Bulletin. The SM will give you the correct part num

number relationship.

Kit 281145D76R00

4 MS20392-4C67 PIN D25286364014 0042

2 MS20392-4C45 PIN D25286364014 0043

4 NAS1149C0532R WASHER D25286364014 0046

6 DAN191-20 RING D25286364014 0047

2 NSA5528-045 CLAMP D25286364014 0065

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM 

1 L32A319-160-002 CONTROL D53370297002 0000

1 L32A319-165-002 ADAPTER D53370297002 0002

2 D5337025020000 ANGLE D53370297002 0006

2 D5337025620200 SECTION D53370297002 0008

1 D5337025620600 SECTION D53370297002 0010

1 D5337025920000 ANGLE D53370297002 0012

1 D5337645020000 BRIDGE D53370297002 0014

1 D5337645300200 BRACKET D53370297002 0016

1 D5337645420000 BRACKET D53370297002 0018

10 MS21919WCH6 CLAMP D53370297002 0030

0.06 ME DAN79-07 HOSE D53370297002 0032

2 NSA935401-03 TIE D53370297002 0034

1 MS20392-2C19 PIN D53370297002 0036

7 NSA5031-3-5 BOLT D53370297002 0040

3 NSA5031-3-4 BOLT D53370297002 0042

1 NAS1726C4P NUT D53370297002 0060

1 NAS509-4C NUT D53370297002 0062

10 NAS1726C3P NUT D53370297002 0064

13 NAS1149C0332R WASHER D53370297002 0070

2 MS24665-153 PIN D53370297002 0080

32 LN9198-3212BF RIVET D53370297002 0632

2 DIN65399-3208BF RIVET D53370297002 0652

1 L32A319-160-002 CONTROL D53370297003 0000

1 L32A319-165-001 ADAPTER D53370297003 0004

78
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

NOTE : Refer to the AIRBUS Standards Manual (SM) if you f

numbers of hardware components in the related kit(

cannot identify in the LIST OF COMPONENTS of this 

Bulletin. The SM will give you the correct part num

number relationship.

Kit 281145D80R00

NOTE : Refer to the AIRBUS Standards Manual (SM) if you f

numbers of hardware components in the related kit(

cannot identify in the LIST OF COMPONENTS of this 

Bulletin. The SM will give you the correct part num

number relationship.

1 D5337645300300 BRACKET D53370297003 0017

1 D5337645420000 BRACKET D53370297003 0018

10 MS21919WCH6 CLAMP D53370297003 0030

0.06 ME DAN79-07 HOSE D53370297003 0032

2 NSA935401-03 TIE D53370297003 0034

1 MS20392-2C19 PIN D53370297003 0036

7 NSA5031-3-5 BOLT D53370297003 0040

3 NSA5031-3-4 BOLT D53370297003 0042

1 NAS1726C4P NUT D53370297003 0060

1 NAS509-4C NUT D53370297003 0062

10 NAS1726C3P NUT D53370297003 0064

13 NAS1149C0332R WASHER D53370297003 0070

2 MS24665-153 PIN D53370297003 0080

32 LN9198-3212BF RIVET D53370297003 0632

2 DIN65399-3208BF RIVET D53370297003 0652

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM 

1 D9259014000000 PANEL D92393242000 0000

4 NAS1096-3-8 SCREW D92393242000 0001

4 NAS1149CN616R WASHER D92393242000 0002

1 NSA931025-03C PLACARD D92393242000 0003

1 D9249226220200 BRACKET D92492261000 0001

1 D9249226200000 BRACKET D92492261000 0002

8 LN9198-4010CF RIVET D92492261000 0640

7 DIN65399-4010CF RIVET D92492261000 0740

79
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

NOTE : Refer to the AIRBUS Standards Manual (SM) if you f

numbers of hardware components in the related kit(

cannot identify in the LIST OF COMPONENTS of this 

Bulletin. The SM will give you the correct part num

number relationship.

Kit 281145D83R01

11 NSA5066-3-1 NUT D93070516000 0060

1 NSA935401-06 TIE D93070516000 0086

1 NSA935401-04 TIE D93070516000 0087

2 LN9198-3210BF RIVET D93070516000 0099

1 D2917091100200 TUBE D93070516000 0120

1 D2707023100000 TUBE D93070516000 0121

1 NSA855006D8 UNION D93070516000 0130

1 D2777000102600 TUBE D93070516000 0135

1 D2777001102400 TUBE D93070516000 0136

1 D2917091100400 TUBE D93070516000 0139

1 D9357045500000 BRACKET D93070516000 0145

1 NSA5586B BLOCK D93070516000 0150

1 NSA935401-05 TIE D93070516000 0151

2 NAS679C06M NUT D93070516000 0165

2 LN9198-3210CF RIVET D93070516000 0198

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM 

7 NAS1096-2-12 SCREW D92491681000 0007

1 NAS1096-2-14 SCREW D92491681000 0009

10 ASNA0113-40ADL WASHER D92491681000 0163

2 D9249102520000 WASHER D92491681000 0190

4 MS21042-08 NUT D92491681000 0202

4 NSA5066-08-1 NUT D92491681000 0230

1 NSA5527-03-04 SPACER D92491681000 0306

1 NSA5527-03-07 SPACER D92491681000 0312

2 A9249187820200 SHEET D92491681000 0565

2 A9249199820000 PLATE D92491681000 0632

2 D9249104720000 GUIDE D92491681000 0724

1 D9249102620600 DEFLECTR D92491681000 0730

6 D9249104920400 BRACKET D92491681000 0737

1 D9249107302800 CONNECTN D92491681000 0824

80
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

NOTE : Refer to the AIRBUS Standards Manual (SM) if you f

numbers of hardware components in the related kit(

cannot identify in the LIST OF COMPONENTS of this 

Bulletin. The SM will give you the correct part num

number relationship.

Kit 281145D84R00

17 D9249179320000 BRACKET D92491681008 0002

1 A9249175120000 ANGLE D92491681008 0003

6 D9249178000600 BRACKET D92491681008 0007

1 D9249177124400 BRACKET D92491681008 0009

5 D9249177520000 ANGLE D92491681008 0013

4 D9249172321200 BRACKET D92491681008 0016

1 D9249172722800 BRACKET D92491681008 0018

1 D9249177520200 ANGLE D92491681008 0019

1 D9249184620400 BRACKET D92491681008 0021

1 D9249177100000 BRACKET D92491681008 0023

1 D9249180922600 BRACKET D92491681008 0026

1 MS21060L3 NUT D92491681008 0027

1 D9249178001200 BRACKET D92491681008 0032

200 LN9198-3215BF RIVET D92491681008 0632

20 LN9198-4828CF RIVET D92491681008 0648

10 DIN65399-2412BF RIVET D92491681008 0724

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM 

18 NAS1801-3-8 SCREW D92491681006 0001

40 NAS1801-08-8 SCREW D92491681006 0003

1 NAS1801-08-19 SCREW D92491681006 0004

19 NAS1149D0332K WASHER D92491681006 0005

40 NAS1149DN816K WASHER D92491681006 0006

18 MS21042L3 NUT D92491681006 0009

16 MS21042L08 NUT D92491681006 0010

1 E0343-01 MOUNT D92491681006 0015

4 D9249177121200 BRACKET D92491681006 0016

1 NSA5527-03-06D SPACER D92491681006 0017

1 D9249177124200 BRACKET D92491681006 0018

1 D9249180800200 BRACKET D92491681006 0024

1 D9249180800400 BRACKET D92491681006 0025

81
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

NOTE : Refer to the AIRBUS Standards Manual (SM) if you f

numbers of hardware components in the related kit(

cannot identify in the LIST OF COMPONENTS of this 

Bulletin. The SM will give you the correct part num

number relationship.

Kit 281145D85R03

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM 

20 NAS1801-08-6 SCREW D92891805000 0004

21 NAS1801-08-9 SCREW D92891805000 0005

4 NAS1801-08-12 SCREW D92891805000 0007

2 NAS1801-08-17 SCREW D92891805000 0010

2 NAS1801-08-19 SCREW D92891805000 0012

2 NAS1801-08-23 SCREW D92891805000 0014

1 NAS1801-08-39 SCREW D92891805000 0020

97 NAS1801-3-9 SCREW D92891805000 0030

8 NAS1100-04-5 SCREW D92891805000 0051

24 NAS1102-08-8 SCREW D92891805000 0058

8 NAS1149CN416R WASHER D92891805000 0150

34 NAS1149CN816R WASHER D92891805000 0152

108 NAS1149C0332R WASHER D92891805000 0153

3 ASNA0113-40ADL WASHER D92891805000 0163

16 NSA935808C01 WASHER D92891805000 0171

1 D9249102520000 WASHER D92891805000 0190

24 MS21042-04 NUT D92891805000 0200

3 MS21042-08 NUT D92891805000 0202

8 MS21042-3 NUT D92891805000 0203

32 NAS1291C3M NUT D92891805000 0218

1 NSA5110-08-1 NUT D92891805000 0225

6 NSA5066-08-1 NUT D92891805000 0230

36 NSA5067-08-1 NUT D92891805000 0236

5 E0343-01 MOUNT D92891805000 0250

10 NSA935504-01 MOUNT D92891805000 0251

1 NSA935504-02 MOUNT D92891805000 0252

3 NSA935513-01 MOUNT D92891805000 0256

6 NSA935513-05 MOUNT D92891805000 0257

1 NSA935513-07 MOUNT D92891805000 0259

6 ABS0355-01 BRACKET D92891805000 0262

82
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

2 NSA5527-03-03 SPACER D92891805000 0304

2 NSA5527-03-04 SPACER D92891805000 0306

4 NSA5527-03-08 SPACER D92891805000 0314

1 NSA5527-03-11 SPACER D92891805000 0320

1 MS21919WCH6 CLAMP D92891805000 0352

12 NSA935807-09 CLAMP D92891805000 0377

4 NSA935807-16 CLAMP D92891805000 0381

4 D9249104800000 SHEET D92891805000 0727

2 D9249104800400 SHEET D92891805000 0729

3 TSTMNR502-0 CONDUIT D92891805000 0763

30 NSA935510-02 BOBBIN D92891805000 0777

100 NSA935401-03 TIE D92891805000 0793

200 NSA935401-04 TIE D92891805000 0794

100 NSA935401-05 TIE D92891805000 0795

1 D9249107100600 STRAP D92891805000 0834

2 DAN328H25 TAPE D92891805000 0877

4 EN2997KE3C12 CAP D92891805000 0930

2 EN2997KE3C16 CAP D92891805000 0932

4 EN2997KE512 CONNECTR D92891805000 0933

2 EN2997KE516 CONNECTR D92891805000 0935

6 D2557016200200 COVER D92891805000 1099

4 D9249104900600 BRACKET D92891805000 1110

2 D9249107303000 CONNECTN D92891805000 0846

8 NAS1801-08-10 SCREW D92891805002 0006

5 NAS1801-08-19 SCREW D92891805002 0012

1 NAS1801-08-25 SCREW D92891805002 0016

1 NAS1096-3-8 SCREW D92891805002 0028

9 NSA935808C01 WASHER D92891805002 0151

12 NAS1149CN816R WASHER D92891805002 0152

1 NAS1149C0332R WASHER D92891805002 0153

1 MS21042L3 NUT D92891805002 0210

12 NSA5066-08-2 NUT D92891805002 0231

3 NSA5527-03-02 SPACER D92891805002 0302

11 NSA5527-03-04 SPACER D92891805002 0306

4 NSA5527-03-06 SPACER D92891805002 0310

11 MS21919WCH4 CLAMP D92891805002 0350

5 MS21919WCH2 CLAMP D92891805002 0364

6 NSA935807-06 CLAMP D92891805002 0376

83
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

266 NSA5066-08-2 NUT D92891805006 0005

5 NSA5527-03-08 SPACER D92891805006 0006

63 MS21042L3 NUT D92891805006 0007

26 MS21042L04 NUT D92891805006 0008

196 NAS1149DN816K WASHER D92891805006 0009

48 NAS1149D0332K WASHER D92891805006 0010

28 NAS1149DN416K WASHER D92891805006 0011

3 NSA935510-02 BOBBIN D92891805006 0012

14 MS21919WCH5 CLAMP D92891805006 0013

11 NSA5527-03-02 SPACER D92891805006 0016

1 NSA935808-01 WASHER D92891805006 0017

10 ABS0731A01 SUPPORT D92891805006 0018

20 NAS1149C0332R WASHER D92891805006 0019

154 NSA5527-03-01 SPACER D92891805006 0020

5 NSA934710T11 FITTING D92891805006 0021

2 NSA934710T14 FITTING D92891805006 0022

1 E0660-01 MOUNT D92891805006 0023

26 NAS1100-04-8 SCREW D92891805006 0025

17 NSA935513-01 MOUNT D92891805006 0027

2 NSA935513-05 MOUNT D92891805006 0028

1 NSA935504-03 MOUNT D92891805006 0030

176 NSA935504-01 MOUNT D92891805006 0031

1 ASNA0032H052 CLAMP D92891805006 0033

5 NSA935513-07 MOUNT D92891805006 0034

41 NSA5527-03-03 SPACER D92891805006 0035

1000 NSA935401-04 TIE D92891805006 0036

17 MS21042L08 NUT D92891805006 0037

1 D9249181406400 GUIDE D92891805006 0038

1 D9249181406600 GUIDE D92891805006 0039

1 NAS1801-3-18 SCREW D92891805006 0040

8 NAS1801-08-14 SCREW D92891805006 0041

1 D9249181404800 GUIDE D92891805006 0042

1 NSA935808C01 WASHER D92891805006 0043

1 D9249181401800 GUIDE D92891805006 0047

4 EN3646A508 RECEPTCL D92891805006 0048

2 ABS0355-03 BRACKET D92891805006 0049

20 NSA5527-03-04 SPACER D92891805006 0052

16 NAS1801-08-10 SCREW D92891805006 0053

84
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

NOTE : Refer to the AIRBUS Standards Manual (SM) if you f

numbers of hardware components in the related kit(

cannot identify in the LIST OF COMPONENTS of this 

Bulletin. The SM will give you the correct part num

number relationship.

Kit 281145D86R00

16 NAS1149D0363K WASHER D92891805006 0060

2 NSA5527-03-15 SPACER D92891805006 0061

1 EN3646A514 RECEPTCL D92891805006 0062

5 E0343-01 MOUNT D92891805006 0063

12 NAS1096-3-10 SCREW D92891805006 0064

3 EN3646A510 RECEPTCL D92891805006 0065

3 EN3646A516 RECEPTCL D92891805006 0066

2 EN3646A3C10 CAP D92891805006 0067

1 EN3646A520 RECEPTCL D92891805006 0068

1 EN3646A522 RECEPTCL D92891805006 0069

200 NSA5539S SLEEVE D92891805006 0070

1 NAS1801-3-44 SCREW D92891805006 0072

200 NSA935401-03 TIE D92891805006 0073

1 NSA5527-03-03 SPACER D92891805006 0075

1 NAS1801-3-28 SCREW D92891805006 0076

1 A9249429720200 BRACKET D92891805006 0078

1 A9249429620400 SEALING D92891805006 0079

0.1 ME NSA939510BN STRIP D92891805006 0080

1 A9249436120000 BRACKET D92891805006 0083

1 NAS1801-3-13 SCREW D92891805006 0084

23 D9249102520000 WASHER D92891805006 0190

1 D9289180520000 PLACARD D92891805006 0200

1 D9289182100800 PLACARD D92891805006

1 D9289182100900 PLACARD D92891805006

QTY UM NEW PART No. KEYWORD DRAWING No. ITEM 

1 D9299140500100 HARNESS D92997043000 0002

1 D9299702600100 EQUIPMNT D92997043000 0004

1 D9299702600200 EQUIPMNT D92997043000 0006

1 D9299142801400 HARNESS D92997043000 0008

1 D9299702800200 EQUIPMNT D92997043000 0010

85
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

D. LIST OF MATERIALS — OPERATOR SUPPLIED

(1) Consumable Materials

1 D9299146201100 HARNESS D92997043000 0024

1 D9299146300400 HARNESS D92997043000 0026

1 D9299146400300 HARNESS D92997043000 0028

1 D9299147000800 HARNESS D92997043000 0030

1 D9299147100600 HARNESS D92997043000 0032

1 D9299147201600 HARNESS D92997043000 0034

1 D9299147300400 HARNESS D92997043000 0036

1 D9299147500700 HARNESS D92997043000 0038

1 D9299148001500 HARNESS D92997043000 0040

1 D9299148100400 HARNESS D92997043000 0042

1 D9299148300800 HARNESS D92997043000 0044

1 D9299149200600 HARNESS D92997043000 0046

1 D9299149300400 HARNESS D92997043000 0048

1 D9299149400400 HARNESS D92997043000 0050

1 D9299704300100 EQUIPMNT D92997043000 0054

1 D9299704300200 EQUIPMNT D92997043000 0056

1 D9299704300300 EQUIPMNT D92997043000 0058

1 D9299704300400 EQUIPMNT D92997043000 0060

1 D9299704300500 EQUIPMNT D92997043000 0062

1 D9299704300600 EQUIPMNT D92997043000 0064

1 D9299704300700 EQUIPMNT D92997043000 0066

1 D9299141900600 HARNESS D92997043000 0072

1 D9299142000600 HARNESS D92997043000 0074

DESCRIPTION REFERENCE TO CML

MAT. No.

QTY PER A/C 

Synth. Ester Based Grease

High Pressure

04-004 As required

Pure Mineral Vaseline 04-012 As required

Putty, Zinc Chromate

General Purpose

05-002 As required

Conductive Film 05-099 As required

Electrical Bonding Coating

(Blue Color)

07-001 As required

Sealant High Temperature 08-007B As required

86
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

(2) Components

None

Sealant, Anaerobic 08013 As required

Two Component Polyurethane

Adhesive

08-025 As required

Adhesive 08-048 As required

Epoxy Resin 08-051 As required

Fuel Tank Sealant

Polysulfide

09-001 As required

Fuel Tank Sealant

Polysulfide

09-002 As required

Corrosion Inhibitive

Interfay Sealant

09-005 As required

Corrosion Inhibiting Brush

Consistency

09-013 As required

Corrosion Inhibiting Fillet

Consistency

09-016 As required

Protective Coating For Fuel

Vapor

09-032 As required

Dry Cleaning Solvent 11-002 As required

Solvent General Purpose 11-026 As required

Corrosion Preventive

Temporary Protective

Compound

15-005 As required

Corrosion Preventive

Temporary Protective

Compound

15-008 As required

Anti-Corrosion Primer

(Polyurethane)

16-001 As required

Polyurethane Top Coat Grey 16-002 As required

Fuel Tank Coating 16-015 As required

External Top Coat

(Polyurethane)

16-018 As required

Lockwire 0.5 mm 19-009 As required

Lockwire 0.6 mm 19-018 As required

Lockwire LN9424A100 None As required

87
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

NOTE (01) Passenger Compartment

NOTE (02) AFT Cargo Compartment

NOTE : For definitions of interchangeability codes in col

to ATA Common Support Data Dictionary (CSDD), Chapt

F. TOOLING — PRICE AND AVAILABILITY

None

G. SPECIAL TOOLS

None

D2587041405000 BLANKET D2587041403000 03 (0

D2587041605000 BLANKET D2587041603000 03 (0

D2587041705000 BLANKET D2587041703000 03 (0

D2587041905000 BLANKET D2587041903000 03 (0

D2587042005200 BLANKET D2587042003000 03 (0

D2587042105200 BLANKET D2587042103000 03 (0

D2587042305000 BLANKET D2587042303000 03 (0

D2587051405000 BLANKET D2587051402400 03 (0

D2587051605000 BLANKET D2587051602200 03 (0

D2587051705000 BLANKET D2587051702200 03 (0

D2587051905000 BLANKET D2587051902200 03 (0

D2587052005200 BLANKET D2587052002200 03 (0

D2587052105200 BLANKET D2587052102200 03 (0

D2587052305000 BLANKET D2587052302200 03 (0

D2587060105200 BLANKET D2587060102000 03 (0

D2587060305200 BLANKET D2587060302200 03 (0

D2587065605000 BLANKET D2587065602000 03 (0

D2587070105200 BLANKET D2587070102000 03 (0

D2587070305200 BLANKET D2587070302000 03 (0

D2587071005400 BLANKET D2587071002000 03 (0

D2587075205000 BLANKET D2587075202200 03 (0

88
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

BEFORE YOU START A TASK ON OR NEAR:

— THE FLIGHT CONTROLS

— THE FLIGHT CONTROL SURFACES

— THE LANDING GEAR AND THE RELATED DOORS

— COMPONENTS THAT MOVE.

CAUTION : ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP 

WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY 

MECHANICALLY SERVICEABLE). WHEN YOU DO MAINTENAN

REPAIRS OR MODIFICATIONS, ALWAYS KEEP ELECTRICA

COMPONENTS AND THE WORK AREA AS CLEAN AS POSSIB

— PUT PROTECTION, SUCH AS PLASTIC SHEETING, CLOT

NECESSARY ON WIRING AND COMPONENTS

— REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATER

CONTAMINATION.

THESE PRECAUTIONS WILL DECREASE THE RISK OF CONT

DAMAGE TO THE ELECTRICAL WIRING INSTALLATION.

IF THERE IS CONTAMINATION, REFER TO ESPM 20-55-0

(1) Preparation

(a) Config. 01

1 Lift the aircraft on jacks, (Refer to AMM 07

block 201).

2 Make sure that the aircraft is electrically g

to AMM 12-34-24 Page block 201).

3 Put the access platform(s) in position.

4 Open the avionics door 822, (Refer to AMM 52

block 201).

5 Open the FWD and AFT cargo compartment doors, 

52-30-00 Page block 201).

89
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

7 Depressurize the Green, Blue and Yellow hydra

(Refer to AMM 29-10-00 Page block 201).

8 Depressurize the reservoirs of the Green, Bl

hydraulic systems, (Refer to AMM 29-14-00 Pag

9 Put warning notices in position to tell perso

pressurize the hydraulic systems.

10 Remove the Green hydraulic reservoir, (Refer 

29-11-41 Page block 401).

11 If necessary, remove the MLG torque tube asse

to AMM 32-33-17 Page block 401).

NOTE : It may be necessary to remove the MLG 

assembly to get access for the replace

fasteners in the ceiling of the MLG ba

and FR43.

12 In the passenger compartment, remove as nece

— the passenger seats, (Refer to AMM 25-21-4

401).

— the textile floor-covering, (Refer to AMM 2

block 401).

— the floor panels, (Refer to AMM 53-32-12 Pa

and AMM 53-42-12 Page block 401).

— the ceiling panels, (Refer to AMM 25-23-41 

401)

— the cove light panels, (Refer to AMM 25-23

401)

— the upper sidewall panels, (Refer to AMM 2

block 401)

— the lower sidewall (dado) panels, (Refer to 

Page block 401)

— the overhead stowage compartments, (Refer t

Page block 401)

90
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

401)

— the ceiling panels, (Refer to AMM 25-54-12 

401)

14 In the AFT cargo compartment, remove as nece

— the ceiling panels, (Refer to AMM 25-55-11 

401)

— the sidewall panels, (Refer to AMM 25-55-1

401)

— the floor panels, (Refer to AMM 53-42-14 Pa

15 Remove the belly fairing panels 147FB, 148FB, 

197GB, 198BB and 198GB, (Refer to AMM 53-35-

401).

NOTE : The belly fairing panels 197AB and 198

replaced in the modification.

16 In the cockpit, remove the lining panels 211H

212KC, 212KW, 212JW and 212HW, (Refer to AMM 

block 001 and AMM 25-13-41 Page block 401).

17 In the forward cargo compartment, remove the 

131AW, 131BW, 131CW, 131DW, 132AW, 131HC, 13

131BC and 131CC, (Refer to AMM 06-41-53 Page 

18 Defuel the center tank, (Refer to AMM 28-25-0

301).

19 Obey the instructions for the fuel safety pro

(Refer to AMM 28-00-00 Page block 301 and AMM 

block 301) and make sure that the ventilation 

tank is correct.

20 On the FUEL section of the HYD/Fuel Panel 40V

that all L TK PUMPS and R TK PUMPS pushbutto

released (the OFF legends are on).

21 Do the preparation procedure as specified in 

removal/installation of the indicator - fuel 

multi-tank (6QT), (Refer to AMM 28-42-22 Page 

91
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

25 Make sure that there is (are) warning notice

external power receptacle to tell persons not 

external power source.

26 Make sure that the EMER EXIT LT pushbutton sw

25VU is set to OFF.

27 In the cockpit, on the ELEC Panel 35VU, relea

pushbutton switches.

28 Put a warning notice in position on the ELEC 

tell persons not to operate the batteries.

29 Put a warning notice in position on the Refue

800VU to tell persons not to operate the NORM

switch.

30 Put a warning notice in position in the cock

persons not to start the APU.

31 Put a warning notice in position in the cock

persons not to operate the fuel system.

32 Put a warning notice in position in the cock

persons not to start the ENG1, 2.

33 Disconnect the battery connectors

a For the job set-up, refer to the removal/i

the batteries, (Refer to AMM 24-38-51 Page 

b Turn the knurled nut a quarter turn.

c Disconnect the connectors.

d Put blanking caps on the disconnected elec

connectors.

34 To route the wires into the Overhead Panel 20

and items of equipment as necessary, but do 

them.

NOTE : Disconnection of the connectors in the 

Panel 20VU will include a high increas

for the test.

92
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

(b) If you find process and material specifications 

drawings which you do not know, refer to the cro

list in the Process and Material Specification 

(c) Refer to the Consumable Material List (CML) for 

specification of the materials (Mat. No.) you mu

Service Bulletin.

(d) For definitions of interchangeability codes in 

refer to the ATA Common Support Data Dictionary 

2 .

(e) For the identification of access panels, (Refer 

06-41-53 Page block 001).

(f) For the frame (FR) identification, (Refer to AMM 

block 001).

(g) Remove the old sealant with a plastic spatula a

surface with Solvent General Purpose (Mat No. 1

(h) For the cleaning of the stripping area, use Solv

Purpose (Mat No. 11-026) .

(i) Remove and install the fasteners, (Refer to SRM 

(j) Torque the standard threaded fasteners, (Refer t

Page block 201).

(k) Wet install fasteners with Corrosion Inhibiting 

Consistency (Mat No. 09-013) .

(l) Drill and deburr the holes, (Refer to SRM 51-44

(m) Countersink the holes, (Refer to SRM 51-46-00).

(n) Cut the rivets to the necessary length.

(o) Clean the surfaces at the location of the placa

Cleaning Solvent (Mat No. 11-002) .

(p) Bond the placards, (Refer to AMM 11-00-00 Page 

(q) Do the sealing and the protection in the center 

to SRM 51-76-12).

93
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

Remove the protection foil before panel installa

aircraft.

Make sure that the protection foil is fully remo

(u) Torque the fasteners of the electrical component

AMM 20-21-15 Page block 201).

(v) Do the electrical bonding (Refer to AMM 20-28-00 

201) with Pure Mineral Vaseline (Mat No. 04-012) 

Electrical Bonding Coating (Blue Color) (Mat No

(w) Put blanking caps on the disconnected electrica

(x) Obey the instructions for the general wiring in

(Refer to ESPM 20-33-00).

(y) To install new wires, cut them to the necessary 

the terminals and connect them.

(z) Route the new wires with the wires that are in t

(aa) Do a continuity test of the new and of the modif

(Refer to ESPM 20-52-21).

(ab) For the cable tie application and tooling, (Refe

20-25-51 and ESPM 20-33-44).

(ac) Install the grounding modules, (Refer to ESPM 20

(ad) Install the connectors, (Refer to ESPM 20-44-22 

20-44-24).

(ae) When you install electrical connectors do a vis

each connector which was disconnected to make s

— the electrical connectors are serviceable befo

them again

— the label of the connector is the same as the 

receptacle

— the connector is correctly locked with Lockwir

No. 19-009) , where locking facilities exists

94
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

(1) Config. 01

NOTE : Remove the finch paint and the paint protectio

extrado panels between Y=+254 and Y=-254 and 

and FR42 and in the center tank. Do not use a 

Do not cause damage to the head of the rivets, 

51-75-11, paragraph 3). Stop the removal when 

the primary protection (green color). Only rem

at the location of the doubler.

(a) Install the doublers on the extrados, in the ce

Refer to Kit 281145A01R01

NOTE : Use a loft to drill the extrado panels :

NOTE : Use Fuel Tank Sealant Polysulfid (Mat No

(b) Install the brackets on the extrados, in the ce

Refer to Kit 281145A01R01

NOTE : Use Fuel Tank Sealant Polysulfid (Mat No

Anti-Corrosion Primer (Mat No. 16-001) , 

Inhibiting Brush Consistency (Mat No. 09

281145A00001 Sheet(s) 01 A00

281145A00001 Sheet(s) 02 A00

281145A00001 Sheet(s) 03 B00

281145A01001 Sheet(s) 01 A00

281145A01001 Sheet(s) 02 A00

281145A01001 Sheet(s) 03 A00

281145A01002 Sheet(s) 01 A00

1 Loft D5713032000095

281145A01003 Sheet(s) 01 A00

281145A01003 Sheet(s) 02 A00

281145A01003 Sheet(s) 03 A00

281145A01003 Sheet(s) 04 A00

281145A01004 Sheet(s) 01 A00

281145A01004 Sheet(s) 02 A00

281145A01004 Sheet(s) 03 A00

281145A01005 Sheet(s) 01 A00

95
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

NOTE : Use Anti-Corrosion Primer (Mat No. 16-001

(d) Install the brackets on the intrados, in the ce

Refer to Kit 281145A02R02

NOTE : Use Fuel Tank Sealant Polysulfid (Mat No

Corrosion Preventive temporary Protective 

No. 15-008) and Anti-Corrosion Primer (M

.

(e) Install the Additional Center Tank (ACT) door a

center tank

Refer to Kit 281145A03R00 and Kit 281145A13R00

1 Remove :

2 Install :

281145A02002 Sheet(s) 01 A00

281145A02002 Sheet(s) 02 A00

281145A02002 Sheet(s) 03 A00

281145A02003 Sheet(s) 01 A00

281145A02003 Sheet(s) 02 A00

281145A03000 Sheet(s) 01 A00

281145A03001 Sheet(s) 01 A00

281145A03002 Sheet(s) 01 A00

281145A03002 Sheet(s) 02 A00

281145A03003 Sheet(s) 01 B00

281145A03004 Sheet(s) 01 A00

281145A03005 Sheet(s) 01 A00

281145A03006 Sheet(s) 01 A00

281145A03007 Sheet(s) 01 A00

281145A13001 Sheet(s) 01 A00

281145A03000 Sheet(s) 01 A00

281145A03001 Sheet(s) 01 A00

281145A03002 Sheet(s) 01 A00

281145A03002 Sheet(s) 02 A00

281145A03003 Sheet(s) 01 B00

281145A03004 Sheet(s) 01 A00

281145A03005 Sheet(s) 01 A00

96
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

(f) Replace the Fuel Quantity Indicator (FQI) 6QT

(Refer to AMM 28-42-22 Page block 401)

1 Remove :

2 Install :

(g) Modify the transfer line in the center tank

Refer to Kit 281145A04R02

1 Remove :

1 Fuel Quantity

Indicator

1407KID02-03

1 Fuel Quantity

Indicator

1418KID01-03

281145A04000 Sheet(s) 01 A00

281145A04001 Sheet(s) 01 A00

281145A04001 Sheet(s) 02 A00

281145A04001 Sheet(s) 03 A00

281145A04002 Sheet(s) 01 A00

281145A04002 Sheet(s) 02 A00

281145A04002 Sheet(s) 03 A00

281145A04002 Sheet(s) 04 A00

281145A04003 Sheet(s) 01 A00

281145A04003 Sheet(s) 02 A00

281145A04003 Sheet(s) 03 A00

281145A04003 Sheet(s) 04 A00

281145A04003 Sheet(s) 05 A00

281145A04004 Sheet(s) 01 A00

281145A04005 Sheet(s) 01 A00

281145A04006 Sheet(s) 01 A00

281145A04007 Sheet(s) 01 A00

281145A04008 Sheet(s) 01 A00

281145A04009 Sheet(s) 01 A00

281145A04010 Sheet(s) 01 A00

281145A04011 Sheet(s) 01 A00

281145A04011 Sheet(s) 02 A00

281145A04012 Sheet(s) 01 A00

281145A04013 Sheet(s) 01 A00

97
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

NOTE : Use Anti-Corrosion Primer (Mat No. 16-

Tank Sealant Polysulfid (Mat No. 09-00

(h) Install the transfer elbow and the air ventilat

the center tank

Refer to Kit 281145A05R00

NOTE : Use Anti-Corrosion Primer (Mat No. 16-001

Coating For Fuel Vapor (Mat No. 09-032) 

Sealant Polysulfid (Mat No. 09-002) , Fue

Polysulfide (Mat No. 09-001) and Fuel Ta

(Mat No. 16-015) .

(i) Apply the sealing protection to the center tank

281145A04002 Sheet(s) 01 A00

281145A04002 Sheet(s) 02 A00

281145A04002 Sheet(s) 03 A00

281145A04002 Sheet(s) 04 A00

281145A04003 Sheet(s) 01 A00

281145A04003 Sheet(s) 02 A00

281145A04003 Sheet(s) 03 A00

281145A04003 Sheet(s) 04 A00

281145A04003 Sheet(s) 05 A00

281145A04004 Sheet(s) 01 A00

281145A04005 Sheet(s) 01 A00

281145A04006 Sheet(s) 01 A00

281145A04007 Sheet(s) 01 A00

281145A04008 Sheet(s) 01 A00

281145A04009 Sheet(s) 01 A00

281145A04010 Sheet(s) 01 A00

281145A04011 Sheet(s) 01 A00

281145A04011 Sheet(s) 02 A00

281145A04012 Sheet(s) 01 A00

281145A04013 Sheet(s) 01 A00

281145A05001 Sheet(s) 01 A00

281145A05002 Sheet(s) 01 A00

281145A05003 Sheet(s) 01 A00

281145A05003 Sheet(s) 02 A00

281145A05003 Sheet(s) 01 A00

281145A05003 Sheet(s) 02 A00

98
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

— Protective Coating For Fuel Vapor (Mat No. 

— Anti-Corrosion Primer (Mat No. 16-001)

— Fuel Tank Coating (Mat No. 16-015) .

(j) Modify the equipment and the wiring in the HYD/

Refer to Kit 281145A06R02 , Kit 281145A07R00 , 

281145A08R00 and Kit 281145A10R01

1 Remove :

2 Install :

NOTE : Secure the screws with Sealant, High T

(Mat No. 08-573) or Sealant, High Tem

No. 08-007B) .

NOTE : The placards are supplied in :

3 Modify the wires

281145A06000 Sheet(s) 01 A00

281145A06001 Sheet(s) 01 A00

281145A06002 Sheet(s) 01 A00

281145A06003 Sheet(s) 01 B00

281145A06004 Sheet(s) 01 A00

281145A06000 Sheet(s) 01 A00

281145A06001 Sheet(s) 01 A00

281145A06002 Sheet(s) 01 A00

281145A06001 Sheet(s) 01 A00

281145A06003 Sheet(s) 01 B00

281145A06004 Sheet(s) 01 A00

Placard Set D9100095114296

281145A10501 Sheet(s) 01 A00

281145A10501 Sheet(s) 03 A00

281145A10502 Sheet(s) 01 A00

281145A10502 Sheet(s) 02 A00

281145A10503 Sheet(s) 01 A00

281145A10503 Sheet(s) 03 A00

99
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

NOTE : The bundle is supplied in Kit 28114

b Attach the wires with :

(k) Modify the equipment and the wiring in the Rear 

121VU and the Rear Panel 120VU

Refer to Kit 281145A06R02 , Kit 281145A09R00 a

281145A10R01

1 Install :

NOTE : The placards are supplied in :

2 Modify the wiring in the Rear Circuit Breake

Bundle D9000095137495

150 Tie-Cable NSA935401-03

150 Tie-Cable NSA935401-06

281145A06005 Sheet(s) 01 A00

Placard Set D9100095114295

281145A06501 Sheet(s) 01 A00

281145A06501 Sheet(s) 02 A00

281145A06502 Sheet(s) 01 A00

281145A06502 Sheet(s) 02 A00

281145A06503 Sheet(s) 01 A00

281145A06503 Sheet(s) 02 A00

281145A06504 Sheet(s) 01 A00

281145A06504 Sheet(s) 02 A00

281145A06505 Sheet(s) 01 A00

281145A06505 Sheet(s) 02 A00

281145A06506 Sheet(s) 01 A00

281145A06506 Sheet(s) 02 A00

281145A06507 Sheet(s) 01 A00

281145A06507 Sheet(s) 02 A00

281145A06508 Sheet(s) 01 A00

281145A06508 Sheet(s) 02 A00

281145A06509 Sheet(s) 01 A00

281145A06509 Sheet(s) 02 A00

281145A06510 Sheet(s) 01 A00

281145A06510 Sheet(s) 02 A00

100
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

b Install the wires :

supplied in :

Install :

FIN 1114PP

between circuit breakers 9QH and 10QH

FIN 1115PP

between circuit breakers 33QU and 34QU

c Attach the wires with :

3 Modify the wiring in the Rear Panel 120VU

() 

281145A06507 Sheet(s) 02 A00

281145A06510 Sheet(s) 02 A00

281145A06502 Sheet(s) 02 A00

281145A06504 Sheet(s) 02 A00

281145A06506 Sheet(s) 02 A00

281145A06508 Sheet(s) 02 A00

281145A06509 Sheet(s) 02 A00

281145A06511 Sheet(s) 02 A00

Bundle D9000095128395

1 Shunt NSA939526-02

1 Shunt NSA939526-02

50 Tie-Cable NSA935401-03

60 Tie-Cable NSA935401-04

40 Tie-Cable NSA935401-05

281145A10501 Sheet(s) 01 A00

281145A10501 Sheet(s) 02 A00

281145A10503 Sheet(s) 01 A00

281145A10503 Sheet(s) 02 A00

281145A10504 Sheet(s) 01 A00

281145A10504 Sheet(s) 02 A00

281145A10505 Sheet(s) 01 A00

101
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

supplied in :

b Attach the wires with :

(l) Modify the routing in the avionics compartment

Refer to Kit 281145A10R01

1 Remove :

2 Install :

281145A10501 Sheet(s) 02 A00

281145A10503 Sheet(s) 02 A00

281145A10504 Sheet(s) 02 A00

281145A10505 Sheet(s) 02 A00

281145A10506 Sheet(s) 02 A00

281145A10507 Sheet(s) 02 A00

Bundle D9000095137395

50 Tie-Cable NSA935401-03

60 Tie-Cable NSA935401-04

20 Tie-Cable NSA935401-05

281145A10001 Sheet(s) 01 A00

281145A10001 Sheet(s) 02 A00

281145A10002 Sheet(s) 01 A00

281145A10002 Sheet(s) 02 A00

281145A10003 Sheet(s) 01 A00

281145A10004 Sheet(s) 01 A00

281145A10004 Sheet(s) 02 A00

281145A10005 Sheet(s) 01 A00

281145A10005 Sheet(s) 02 A00

281145A10006 Sheet(s) 01 A00

281145A10006 Sheet(s) 02 A00

281145A10001 Sheet(s) 01 A00

281145A10001 Sheet(s) 02 A00

281145A10002 Sheet(s) 01 A00

281145A10002 Sheet(s) 02 A00

281145A10003 Sheet(s) 01 A00

281145A10004 Sheet(s) 01 A00

281145A10004 Sheet(s) 02 A00

102
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

NOTE : Use Anti-Corrosion Primer (Mat No. 16

Polyurethane Top Coat Grey (Mat No. 16

Corrosion Inhibiting Fillet Consistenc

09-016) .

(m) Modify the equipment in the FWD cargo compartme

Refer to Kit 281145A10R01

1 Install :

NOTE : The placards are supplied in :

(n) Modify the wiring in the avionics compartment a

cargo compartment

Refer to Kit 281145A10R01

281145A10007 Sheet(s) 01 A00

281145A10007 Sheet(s) 02 A00

Placard Set D9100095116795

281145A10501 Sheet(s) 01 A00

281145A10501 Sheet(s) 07 B00

281145A10502 Sheet(s) 01 A00

281145A10502 Sheet(s) 07 B00

281145A10503 Sheet(s) 01 A00

281145A10503 Sheet(s) 05 B00

281145A10504 Sheet(s) 01 A00

281145A10504 Sheet(s) 05 B00

281145A10505 Sheet(s) 01 A00

281145A10505 Sheet(s) 04 B00

281145A10506 Sheet(s) 01 A00

281145A10506 Sheet(s) 05 B00

281145A10507 Sheet(s) 01 A00

281145A10507 Sheet(s) 04 B00

281145A10508 Sheet(s) 01 B00

281145A10508 Sheet(s) 03 B00

281145A10509 Sheet(s) 01 A00

281145A10509 Sheet(s) 03 B00

281145A10510 Sheet(s) 01 A00

281145A10510 Sheet(s) 03 B00

103
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

supplied in :

(o) Modify the wiring between the avionics compartme

cockpit

Refer to Kit 281145A10R01

1 Install the wires :

supplied in :

() 

281145A10504 Sheet(s) 05 B00

281145A10505 Sheet(s) 04 B00

281145A10506 Sheet(s) 05 B00

281145A10507 Sheet(s) 04 B00

281145A10508 Sheet(s) 03 B00

281145A10509 Sheet(s) 03 B00

281145A10510 Sheet(s) 03 B00

281145A10519 Sheet(s) 04 B00

Bundle D9000095137996

281145A10501 Sheet(s) 01 A00

281145A10501 Sheet(s) 08 A00

281145A10502 Sheet(s) 01 A00

281145A10502 Sheet(s) 06 A00

281145A10503 Sheet(s) 01 A00

281145A10503 Sheet(s) 06 A00

281145A10504 Sheet(s) 01 A00

281145A10504 Sheet(s) 06 A00

281145A10505 Sheet(s) 01 A00

281145A10505 Sheet(s) 05 A00

281145A10506 Sheet(s) 01 A00

281145A10506 Sheet(s) 06 A00

281145A10507 Sheet(s) 01 A00

281145A10507 Sheet(s) 05 A00

281145A10501 Sheet(s) 08 A00

281145A10502 Sheet(s) 06 A00

281145A10503 Sheet(s) 06 A00

281145A10504 Sheet(s) 06 A00

281145A10505 Sheet(s) 05 A00

281145A10506 Sheet(s) 06 A00

281145A10507 Sheet(s) 05 A00

104
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

NOTE : The placards are supplied in :

2 Modify the wiring

a Install the wires :

supplied in :

b Attach the wires with :

(q) Modify the equipment and the wiring in the Conta

Refer to Kit 281145A10R01

1 Install :

NOTE : The placards are supplied in :

281145A10008 Sheet(s) 01 A00

281145A10008 Sheet(s) 02 A00

281145A10008 Sheet(s) 03 A00

Placard Set D9100095116795

281145A10502 Sheet(s) 01 A00

281145A10502 Sheet(s) 03 A00

281145A10506 Sheet(s) 01 A00

281145A10506 Sheet(s) 03 A00

281145A10519 Sheet(s) 01 A00

281145A10519 Sheet(s) 02 A00

281145A10502 Sheet(s) 03 A00

281145A10506 Sheet(s) 03 A00

281145A10519 Sheet(s) 02 A00

Bundle D9000095137695

60 Tie-Cable NSA935401-04

60 Tie-Cable NSA935401-05

120 Tie-Cable NSA935401-06

240 Tie-Cable NSA935401-08

281145A10009 Sheet(s) 01 A00

281145A10009 Sheet(s) 02 A00

105
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

a Install the wires :

supplied in :

b Attach the wires with :

(r) Modify the equipment and the wiring in the AFT 

Rack 80VU

Refer to Kit 281145A10R01

1 Install :

2 Modify the wiring

281145A10505 Sheet(s) 03 A00

281145A10501 Sheet(s) 04 A00

281145A10505 Sheet(s) 03 A00

Bundle D9000095137595

60 Tie-Cable NSA935401-04

60 Tie-Cable NSA935401-05

120 Tie-Cable NSA935401-06

240 Tie-Cable NSA935401-08

281145A10010 Sheet(s) 01 A00

281145A10010 Sheet(s) 01 A00

281145A10501 Sheet(s) 01 A00

281145A10501 Sheet(s) 06 A00

281145A10502 Sheet(s) 01 A00

281145A10502 Sheet(s) 05 A00

281145A10504 Sheet(s) 01 A00

281145A10504 Sheet(s) 04 A00

281145A10510 Sheet(s) 01 A00

281145A10510 Sheet(s) 02 A00

281145A10511 Sheet(s) 01 A00

281145A10511 Sheet(s) 02 A00

281145A10512 Sheet(s) 01 A00

281145A10512 Sheet(s) 02 A00

281145A10513 Sheet(s) 01 A00

281145A10513 Sheet(s) 02 A00

106
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

b Install the wires :

supplied in :

c Attach the wires with :

(s) Modify the equipment and the wiring in the FWD 

Rack 90VU

Refer to Kit 281145A10R01 , Kit 281145A11R03 a

281145A12R00

1 Remove the Shelf 92VU

a From the Shelf 92VU, remove for access the 

7QJ, 9QJ, 3QT and 24XG :

(Refer to AMM 24-41-34 Page block 401)

(Refer to AMM 28-42-34 Page block 401)

(Refer to AMM 28-46-34 Page block 401)

() 

281145A10513 Sheet(s) 02 A00

281145A10501 Sheet(s) 06 A00

281145A10502 Sheet(s) 05 A00

281145A10504 Sheet(s) 04 A00

281145A10510 Sheet(s) 02 A00

281145A10512 Sheet(s) 02 A00

281145A10514 Sheet(s) 02 A00

281145A10515 Sheet(s) 02 A00

Bundle D9000095137895

60 Tie-Cable NSA935401-04

60 Tie-Cable NSA935401-05

120 Tie-Cable NSA935401-06

240 Tie-Cable NSA935401-08

1 FLSCU1 

1 FLSCU2 

1 FQIC 

1 GAPCU 

107
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

d Remove the Shelf 92VU and install it on be

2 Remove the Shelf 93VU

a From the Shelf 93VU, remove for access the 

1CE3, 5GA1 and 8HK :

(Refer to AMM 21-63-34 Page block 401)

(Refer to AMM 27-94-34 Page block 401)

(Refer to AMM 32-31-71 Page block 401)

NOTE : You must install these computers ag

modification of the wiring.

b Disconnect the bonding braid.

c Remove the attachment hardware from the S

NOTE : Retain the hardware.

d Remove the Shelf 93VU and install it on be

3 Remove the Shelf 94VU

a From the Shelf 94VU, remove for access the 

5GA2, 10GG, 10HC and 10WQ :

(Refer to AMM 21-43-34 Page block 401)

(Refer to AMM 26-17-34 Page block 401)

(Refer to AMM 32-31-71 Page block 401)

(Refer to AMM 32-42-34 Page block 401)

1 SEC3 

1 LGCIU1 

1 ZONE CONT 

1 LGCIU2 

1 BSCU 

1 HEAT CONT 

1 SDCU 

108
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

d Remove the Shelf 94VU and install it on be

4 On the Shelf 92VU

a Remove :

b Install :

NOTE : The placards are supplied in :

5 On the Shelf 94VU

a Install :

NOTE : The placards are supplied in :

6 Modify the wiring

281145A11000 Sheet(s) 01 B00

281145A11001 Sheet(s) 01 A00

281145A11002 Sheet(s) 01 B00

281145A11003 Sheet(s) 01 A00

Placard Set D9100095116895

281145A11004 Sheet(s) 01 A00

281145A11004 Sheet(s) 02 A00

Placard Set D9100095116895

281145A10501 Sheet(s) 01 A00

281145A10501 Sheet(s) 05 A00

281145A10502 Sheet(s) 01 A00

281145A10502 Sheet(s) 04 A00

281145A10503 Sheet(s) 01 A00

281145A10503 Sheet(s) 04 A00

281145A10504 Sheet(s) 01 A00

281145A10504 Sheet(s) 03 A00

281145A10506 Sheet(s) 01 A00

281145A10506 Sheet(s) 04 A00

281145A10507 Sheet(s) 01 A00

281145A10507 Sheet(s) 03 A00

281145A10508 Sheet(s) 01 B00

281145A10508 Sheet(s) 02 A00

109
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

a Remove the wires :

b Install the wires :

supplied in :

c Attach the wires with :

7 Install the Shelf 92VU

a Install the Shelf 92VU on aircraft.

281145A10518 Sheet(s) 02 A00

281145A10519 Sheet(s) 01 A00

281145A10519 Sheet(s) 03 A00

281145A10520 Sheet(s) 01 A00

281145A10520 Sheet(s) 02 A00

281145A10521 Sheet(s) 01 A00

281145A10521 Sheet(s) 02 A00

281145A10522 Sheet(s) 01 A00

281145A10522 Sheet(s) 02 A00

281145A10516 Sheet(s) 02 A00

281145A10518 Sheet(s) 02 A00

281145A10520 Sheet(s) 02 A00

281145A10521 Sheet(s) 02 A00

281145A10501 Sheet(s) 05 A00

281145A10502 Sheet(s) 04 A00

281145A10503 Sheet(s) 04 A00

281145A10504 Sheet(s) 03 A00

281145A10506 Sheet(s) 04 A00

281145A10507 Sheet(s) 03 A00

281145A10508 Sheet(s) 02 A00

281145A10509 Sheet(s) 02 A00

281145A10517 Sheet(s) 02 A00

281145A10519 Sheet(s) 03 A00

281145A10522 Sheet(s) 02 A00

Bundle D9000095137795

60 Tie-Cable NSA935401-04

60 Tie-Cable NSA935401-05

120 Tie-Cable NSA935401-06

240 Tie-Cable NSA935401-08

110
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

and 24XG :

(Refer to AMM 24-41-34 Page block 401)

(Refer to AMM 28-42-34 Page block 401)

(Refer to AMM 28-46-34 Page block 401)

NOTE : These computers were retained at re

8 Install the Shelf 93VU

a Install the Shelf 93VU on aircraft.

b Do the electrical bonding on the shelf att

c Attach the Shelf 93VU and connect the bond

the hardware retained at removal.

NOTE : Retain the hardware.

d On the Shelf 93VU, install the computers 

8HK :

(Refer to AMM 21-63-34 Page block 401)

(Refer to AMM 27-94-34 Page block 401)

(Refer to AMM 32-31-71 Page block 401)

NOTE : These computers were retained at re

9 Install the Shelf 94VU

a Install the Shelf 94VU on aircraft.

b Do the electrical bonding on the shelf att

1 FLSCU1

1 FLSCU2

1 FQIC

1 GAPCU

1 SEC3

1 LGCIU1

1 ZONE CONT

111
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

(Refer to AMM 21-43-34 Page block 401)

(Refer to AMM 26-17-34 Page block 401)

(Refer to AMM 32-31-71 Page block 401)

(Refer to AMM 32-42-34 Page block 401)

NOTE : These computers were retained at re

(2) Config. 01 , Kit 281145B01R00

Refer to drawings :

(a) Install the equipment for the ACT pressurizatio

between FR48 and FR54.

1 Install these items at the crossbeam at FR54 

drawing D28270975, sheet 7 and Sections A7-A8 

(3) Config. 01 , Kit 281145B02R00

Refer to drawings :

(a) Install this item in the forward avionics compa

(4) Config. 01 , Kit 281145B02R00 , Kit 281145B03R00 and 

281145B04R00

1 LGCIU2

1 BSCU

1 HEAT CONT

1 SDCU

D28270975 Sheet(s) 7 thru 12

1 Filter QB0566 Item 41

1 Valve HTE490005 Item 42

1 Actuator HTE200002-1 Item 43

1 Valve HTE920007-001 Item 44

1 Clamp HTE8002 Item 45

1 Valve PAS148-133A Item 46

1 Valve HTE490005 Item 47

D92355000 Sheet(s) 1

D92556025 Sheet(s) 1 and 3

1 Relay box D9255602500400

112
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

() /p

in the belly fairing, zone 192.

1 Remove the pre-select unit 5QT (Refer to AMM 

block 401).

2 Remove the refuel/defuel control panel 800VU 

28-25-55 Page block 401).

3 Remove the fuel quantity indicator unit 6QT 

28-42-22 Page block 401).

4 Temporarily remove all attachments and assoc

from the panel mounting-assembly.

5 Remove the panel mounting-assembly, retain t

bolts for installation of the new panel mount

in the same position.

(b) Install additional wiring between zone 192 and 

1 Install the wires shown on lines 1 thru 14 of 

Chart (Refer to Figure 1 Sheet 1 ).

supplied in :

and route them with the wires that are in the 

NOTE : The existing wire shown on line 3 can 

it is of sufficient length or it can b

the new wire installed.

2 Cut the wires to the necessary length, crimp 

and connect them.

3 Attach the wires with tie-wraps as necessary

4 Do an intrinsically safe continuity test of t

(c) Install the new refuel/defuel panel mounting as

belly fairing, zone 192.

1 Use a non-metallic spatula to remove the sea

the areas with Solvent General Purpose (Mat N

1 Bundle D92400000647

113
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

3 Install all the attachment and associated fit

from the panel mounting-assembly.

4 Install the pre-select unit 5QT (Refer to AMM 

block 401).

5 Install the refuel/defuel control panel 800VU 

28-25-55 Page block 401).

6 Install the fuel quantity indicator unit 6QT 

28-42-22 Page block 401).

7 Install the refuel panel assembly 801VU

Refer to drawing D92550025 and install this 

(5) Config. 01

Refer to Kit 281145D01R00 thru Kit 281145D86R00

(a) Remove the inflation reservoirs 7506MM and 7507M

and RH offwing escape slides.

(Refer to AMM 25-62-46 Page block 401).

Refer to drawing(s) :

(b) In the AFT cargo compartment, remove the placard

inflation reservoir access.

(Refer to AMM 11-00-00 Page block 201).

Refer to drawing(s) :

(c) Install the MOD/SB placards.

Refer to Kit 281145D70R00

1 Panel

Assy-Refuel,

800VU

D9255003200400

1 Panel

Assy-Refuel,801VU

D9255002500200

D25690000004 Sheet(s) 7 - 9

D25573522000 Sheet(s) 1

114
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

Refer to drawing(s) :

(e) Between FR45 and FR48 (LH and RH), install the o

slide reservoirs and associated pressure tubes.

Refer to Kit 281145D74R00

1 When you accomplish this workstep, remove, mo

install the insulation blankets after the bra

installation. For the re-identification of t

blankets, refer to paragraph 2.E.

2 Install the support brackets for the reservo

associated pressure tubes for the off-wing e

system.

Refer to drawing(s) :

3 Install the pressure tubes between FR45 and 

RH).

Refer to drawing(s) :

NOTE : This drawing contains the consumable m

— Putty, Zinc Chromate General Purpose 

05-002) .

4 Install the inflation reservoirs 7784MM and 

Refer to drawing(s) :

NOTE : This drawing contains the consumable m

— Synth. Ester Based Grease High Press

04-004) .

D92894736004 Sheet(s) 14 - 17

D92992293014 Sheet(s) 16

D92992293016 Sheet(s) 17

D25670762000 Sheet(s) 1 - 7

D25671745000 Sheet(s) 1 - 7

D25671746000 Sheet(s) 1 - 4

115
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REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

Refer to drawing(s) :

2 Install the placards on the doors of the OHSC

Refer to drawing(s) :

(g) Relocate the release cables for the LH and RH of

slides.

Refer to Kit 281145D76R00 .

(Refer to AMM 25-62-43 Page block 401).

1 Relocate the flexible control assembly for t

escape slide.

Refer to drawing(s) :

NOTE : This drawing contains these consumable 

— Lockwire LN9424A100

— Corrosion Inhibitive Interfay Sealan

09-005)

— Synth. Ester Based Grease High Press

04-004)

— Adhesive (Mat No. 08-048)

— Conductive Film (Mat No. 05-099)

2 Relocate the flexible control assembly for t

escape slide.

Refer to drawing(s) :

NOTE : This drawing contains these consumable 

D25286364014 Sheet(s) 7 and 8

D25288767000 Sheet(s) 1 and 2

D53370297002 Sheet(s) 1 - 7

D53370297003 Sheet(s) 1 - 7

116
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

— Adhesive (Mat No. 08-048)

— Conductive Film (Mat No. 05-099)

(h) Do the structural modification for the ACT 1 and 

provisions in the center fuselage.

Refer to Kit 281145D05R00 .

Refer to drawing(s) :

NOTE : It is not necessary to modify and reuse I

0207. New components are supplied in the 

281145D05R00 .

(i) Do the structural modification for the ACT 1 pro

AFT cargo compartment between FR48 and FR53.

Refer to Kit 281145D40R01 .

Refer to drawing(s) :

NOTE : For installation of the bracket, Item 102

rivets ASNA0082B3 (quantity 12) can be u

Sheet 16, Section B16-B16.

(j) Do the structural modification for the ACT 2 pro

AFT cargo compartment between FR52 and FR54.

Refer to Kit 281145D06R00 .

Refer to drawing(s) :

(k) Install the angles on the webs of the keel beam

and FR46

Refer to Kit 281145D07R00

Refer to drawing(s) :

D53372362006 Sheet(s) 1, 4 - 9 and 12 - 

D53470075004 Sheet(s) 1 - 4, 6 - 17

D53470076004 Sheet(s) 1 - 10

D53370780004 Sheet(s) 2

117
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

(m) Replace the fasteners at FR52, FR53 and FR54, be

and STGR36 (LH).

Refer to Kit 281145D08R00

Refer to drawing(s) :

(n) Replace the belly fairing panels 197AB and 198G

modification to the attachment structure.

Refer to Kit 281145D04R00

(Refer to AMM 53-35-13 Page block 401).

Refer to drawing(s) :

(o) Do the modification to the passenger compartment 

structure between FR42 and FR46.

Refer to Kit 281145D61R00

Refer to drawing(s) :

(p) Replace the fasteners between FR42 and FR44 (LH)

Refer to Kit 281145D62R00

Refer to drawing(s) :

(q) Replace the fasteners between FR42 and FR44 (RH)

Refer to Kit 281145D63R00

Refer to drawing(s) :

D53470096002 Sheet(s) 1

D53475024000 Sheet(s) 1 - 6

D53371046000 Sheet(s) 1 - 5

D53371237000 Sheet(s) 1

D53371237001 Sheet(s) 1

118
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REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

(Refer to AMM 25-52-34 Page block 401).

(Refer to AMM 25-55-41 Page block 401).

Refer to drawing(s) :

NOTE : Retain the power drive units, the XZ latc

plugs, the spacers, the divider net and t

(s) Remove the roller tracks.

(Refer to AMM 25-52-21 Page block 401).

Refer to drawing(s) :

(t) Remove the servo mechanism and actuator.

(Refer to AMM 25-52-51 Page block 401).

Refer to drawing(s) :

NOTE : Retain the servo mechanism and actuator a

components. Discard the attaching hardwa

(u) Remove the entrance guides, the YZ latch assemb

rail.

(Refer to AMM 25-52-48 Page block 401).

(Refer to AMM 25-52-44 Page block 401).

Refer to drawing(s) :

(v) Install the roller tracks and YZ latch assemblie

Refer to Kit 281145D42R03

Refer to drawing(s) :

D25572585000 Sheet(s) 1, 2, 7 and 23

D25572585002 Sheet(s) 3 - 5

D25572585004 Sheet(s) 6

D25572585006 Sheet(s) 8 - 10

119
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

(w) Install the servo mechanism and actuator.

Refer to Kit 281145D43R00

Refer to drawing(s) :

NOTE : This drawing contains this consumable mat

— Synth. Ester Based Grease High Pressure 

04-004) .

(x) Install the shim plates on the floor framework 

and FR59.

Refer to Kit 281145D44R01

Refer to drawing(s) :

NOTE : The quantity of shims at each position i

the results of the roller track levelling

paragraph 3.B.(5)(bo).

(y) Apply corrosion preventative to the roller trac

Refer to drawing(s) :

NOTE : Use Corrosion Preventive Temporary Prote

(Mat No. 15-005) .

(z) Attach the cable harnesses to the structure betw

FR54A.

Refer to Kit 281145D48R00

Refer to drawing(s) :

(aa) Remove the Tie Down Points for the cargo nets at 

FR56 and on the roller track at FR50, FR53, FR5

D25572585014 Sheet(s) 24 and 25

D25572585016 Sheet(s) 26

D25572585018 Sheet(s) 27

D25572585026 Sheet(s) 28 and 29

120
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REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

Refer to Kit 281145D46R00

Refer to drawing(s) :

(ac) Install the ball mats and ball strips between F

Refer to Kit 281145D47R01

Refer to drawing(s) :

NOTE : This drawing contains the consumable mate

— Corrosion Inhibiting Brush Consistency 

09-013) .

(ad) Install the X-latch, latch rail, guide rails and 

between FR53 and FR58.

Refer to Kit 281145D49R01

Refer to drawing(s) :

(ae) Install the cargo nets in the AFT cargo compartm

Refer to Kit 281145D52R00

Refer to drawing(s) :

(af) Remove the placards on the sidewall panels in t

compartment.

Refer to drawing(s) :

(ag) Install the placards on the sidewall panels in t

compartment.

D25572585022 Sheet(s) 31

D25572585024 Sheet(s) 32 and 33

D25572585028 Sheet(s) 34 and 35

D25572585034 Sheet(s) 36

D25572585036 Sheet(s) 37

121
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REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

(ah) After the adjustment of the roller tracks remove 

the XZ latches at FR50 and FR53.

Refer to drawing(s) :

(ai) Install the XZ latch 32ACT in the center roller 

and FR53.

Refer to Kit 281145D50R00

Refer to drawing(s) :

(aj) Do the modification to the attachment structure 

cargo-compartment sidewall and partition panels

Refer to Kit 281145D36R00

Refer to drawing(s) :

NOTE : This drawing contains the consumable mate

— Corrosion Inhibiting Fillet Consistency 

09-016) .

(ak) In the AFT cargo compartment replace the floor 

152SF, 151TF, 152TF, 151AG, 152AG, 151BG and 15

Refer to Kit 281145D33R00

(Refer to AMM 53-42-14 Page block 401).

Refer to drawing(s) :

(al) Seal the gaps between the cargo compartment floo

151SF, 152SF, 151TF, 152TF, 151AG, 152AG, 151BG 

Refer to Kit 281145D34R00

Refer to drawing(s) :

D25572585038 Sheet(s) 39

D25572585030 Sheet(s) 40

D53975019000 Sheet(s) 1 - 6

D53675510000 Sheet(s) 1 - 3

122
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

(am) Replace the insulation blankets between FR46 and 

Refer to Kit 281145D10R00

(Refer to AMM 25-80-00 Page block 201).

Refer to drawing(s) :

(an) In the AFT cargo compartment, replace the ceili

151AC, 151BC and 151GC.

Refer to Kit 281145D25R00

(Refer to AMM 25-55-11 Page block 401).

Refer to drawing(s) :

(ao) In the AFT cargo compartment, replace the sidewa

151CW, 151EW and 151HW.

Refer to Kit 281145D26R00

(Refer to AMM 25-55-11 Page block 401).

Refer to drawing(s) :

(ap) In the AFT cargo compartment, replace the sidewa

152CW and 152DW.

Refer to Kit 281145D27R00

(Refer to AMM 25-55-11 Page block 401).

Refer to drawing(s) :

(aq) In the AFT cargo compartment at FR47, replace t

panels 151BW, 151AW and 152BW.

Refer to Kit 281145D28R00

D25870003048 Sheet(s) 20

D25571073000 Sheet(s) 1

D25571073002 Sheet(s) 2

D25571073004 Sheet(s) 3

123
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REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

Refer to Kit 281145D31R00

(Refer to AMM 53-32-12 Page block 401 and AMM 5

block 401).

Refer to drawing(s) :

(as) Seal the gaps between the passenger compartment 

241JF, 251BF, 252BF, 252CF, 251GF, 251FF, 252GF 

Refer to Kit 281145D32R00

Refer to drawing(s) :

NOTE : This drawing contains the consumable mate

— Corrosion Inhibiting Fillet Consistency 

09-016) .

(at) Install the fuel vent line between FR37 and FR4

transfer line between FR41 and FR47.

Refer to Kit 281145D13R01

Refer to drawing(s) :

NOTE : This drawing contains the consumable mate

— Lockwire 0.6 mm (Mat No. 19-018) .

(au) Install the shroud drain system between FR37 and 

Refer to Kit 281145D11R00 and Kit 281145D14R00

1 Install the support brackets on the Green hyd

reservoir support.

Refer to Kit 281145D11R00

Refer to drawing(s) :

D53675015002 Sheet(s) 3 and 4

D53675016002 Sheet(s) 3 and 4

D28270972002 Sheet(s) 7 - 12

124
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

NOTE : This drawing contains the consumable m

— Corrosion Inhibiting Fillet Consiste

09-016)

— Two Component Epoxy Adhesive (Mat No

(av) Install the ACT 1 cavity drain and monitoring sy

FR46 and FR50.

Refer to Kit 281145D15R00

Refer to drawing(s) :

NOTE : This drawing contains the consumable mate

— Corrosion Inhibiting Fillet Consistency 

09-016)

— Two Component Epoxy Adhesive (Mat No. 0

NOTE : Do not tighten the cap, Item 0033 (instal

FR50 and FR51). This is removed when you 

ACT 2 cavity drain and monitoring system

(aw) Install the ACT 1 pressurization system between 

Refer to Kit 281145D16R01

Refer to drawing(s) :

NOTE : The Items 0041 thru 0047 referenced on th

supplied and installed with Kit 281145B01

paragraph 3.B.(2)(a).

NOTE : Do not tighten the cap, Item 0094 (instal

FR51 and FR52). This is removed when you 

ACT 2 pressurization system.

D28270973002 Sheet(s) 6 - 10

D28270974002 Sheet(s) 4 - 6

D28270975004 Sheet(s) 8, 10, 11, 13 - 1

125
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

(ay) Install the ACT 2 cavity drain and monitoring sy

FR50 and FR53.

Refer to Kit 281145D01R00

Refer to drawing(s) :

(az) Install the ACT 2 pressurization system between 

Refer to Kit 281145D02R00

Refer to drawing(s) :

(ba) Install the support brackets for the pressurizat

drain systems between FR51 and FR53

Refer to Kit 281145D03R00

Refer to drawing(s) :

(bb) Install the beam between FR46 and FR47.

Refer to Kit 281145D18R00

Refer to drawing(s) :

(bc) Install the switching panel 2028VU.

Refer to Kit 281145D80R00

Refer to drawing(s) :

(bd) Install the cover between FR46 and FR47 at the f

and vent lines.

D28270990002 Sheet(s) 2 and 4

D28270991000 Sheet(s) 1 - 3

D28270992000 Sheet(s) 1 - 4

D28270998002 Sheet(s) 2

D92393242000 Sheet(s) 1

D92492261000 Sheet(s) 1

126
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REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

Refer to Kit 281145D20R00

Refer to drawing(s) :

(bf) Do the modification to the support brackets on f

in the passenger compartment, between FR41 and 

between FR49 and FR55.

Refer to Kit 281145D83R01

Refer to drawing(s) :

(bg) Replace the support bracket at FR42.

Refer to Kit 281145D83R01

Refer to drawing(s) :

(bh) Do the modification to the support bracket insta

AFT cargo compartment between FR47 and FR55

Refer to Kit 281145D84R00

Refer to drawing(s) :

(bi) Do the modification to the support bracket insta

between FR46 and FR52 and FR54.

Refer to Kit 281145D83R01

Refer to drawing(s) :

NOTE : This drawing contains the consumable mate

— Corrosion Inhibiting Brush Consistency 

09-013) .

D28270515000 Sheet(s) 1 - 4

D92491681000 Sheet(s) 1 - 6

D92491681002 Sheet(s) 7 - 9

D92491681006 Sheet(s) 34 - 45

D92491681008 Sheet(s) 10, 12 - 24, 26, 

127
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

NOTE : This drawing contains the consumable mate

— Sealant, Anaerobic (Mat No. 08-013) .

(bk) Do the modification to the attachment parts for 

harnesses at FR42.

Refer to Kit 281145D85R03

Refer to drawing(s) :

.

For additional information concerning bonding po

DC2, 6989VN B1, 7309VN DC1, 7332VN B2 and 7334VN 

Refer to drawing(s) :

(bl) Do the modification to the attachment parts for 

harnesses between FR46 and FR55.

Refer to Kit 281145D85R03

Refer to drawing(s) :

NOTE : This drawing contains the consumable mate

— Corrosion Inhibiting Fillet Consistency 

09-016)

— Adhesive (Mat No. 08-048)

— Two Component Epoxy Adhesive (Mat No. 0

— Two Component Polyurethane Adhesive (Ma

— Transparent Protective Coating (Mat No

D92891805000 Sheet(s) 1 - 15

D92891805002 Sheet(s) 16 - 19

D92891120000 Sheet(s) 9 and 33

D92891805006 Sheet(s) 20, 22 - 31, 39 - 

50 - 52

128
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

1 Replace the cable harness 4605VB.

Refer to drawing(s) :

2 Do the modification to the cable harness 4606

Refer to drawing(s) :

3 Do the modification to the cable harness 460

Refer to drawing(s) :

4 Replace the cable harness 4628VB

Refer to drawing(s) :

5 Do the modification to the cable harness 4640

Refer to drawing(s) :

6 Do the modification to the cable harness 4644

Refer to drawing(s) :

7 Do the modification to the cable harness 4648

Refer to drawing(s) :

8 Do the modification to the cable harness 4650

D92991405000 Sheet(s) 1

D92991405001 Sheet(s) 2

D92997026001 Sheet(s) 1 and 2

D92997026002 Sheet(s) 3 - 8

D92991428013 Sheet(s) 18, H013

D92991428014 Sheet(s) 19, H014

D92997028002 Sheet(s) 1 and 2

D92997028004 Sheet(s) 3 and 4

D92997028006 Sheet(s) 5 and 6

129
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REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

10 Replace the cable harness 4661VB.

Refer to drawing(s) :

11 Replace the cable harness 4662VB.

Refer to drawing(s) :

12 Replace the cable harness 4663VB.

Refer to drawing(s) :

13 Replace the cable harness 4664VB.

Refer to drawing(s) :

14 Replace the cable harness 4670VB.

Refer to drawing(s) :

15 Replace the cable harness 4671VB.

Refer to drawing(s) :

D92991456004 Sheet(s) 5, H004

D92991456005 Sheet(s) 4, H005

D92991461021 Sheet(s) 26, H021

D92991461022 Sheet(s) 27, H022

D92991462010 Sheet(s) 10, H010

D92991462011 Sheet(s) 11, H011

D92991463003 Sheet(s) 8, H003

D92991462011 Sheet(s) 10, H004

D92991464002 Sheet(s) 4, H002

D92991464003 Sheet(s) 5, H003

D92991470007 Sheet(s) 8, H007

D92991470008 Sheet(s) 9, H008

D92991471005 Sheet(s) 7, H005

D92991471006 Sheet(s) 8, H006

130
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REVISION No. : 01 — Apr 27/07 Page :

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17 Replace the cable harness 4673VB.

Refer to drawing(s) :

18 Replace the cable harness 4675VB.

Refer to drawing(s) :

19 Replace the cable harness 4680VB.

Refer to drawing(s) :

20 Replace the cable harness 4681VB.

Refer to drawing(s) :

21 Replace the cable harness 4683VB.

Refer to drawing(s) :

22 Replace the cable harness 4692VB.

Refer to drawing(s) :

23 Replace the cable harness 4693VB.

D92991472014 Sheet(s) 15, H014

D92991472016 Sheet(s) 16, H016

D92991473003 Sheet(s) 4, H003

D92991473004 Sheet(s) 3, H004

D92991475006 Sheet(s) 7, H006

D92991475007 Sheet(s) 8, H007

D92991480014 Sheet(s) 15, H014

D92991480015 Sheet(s) 16, H015

D92991481003 Sheet(s) 4, H003

D92991481004 Sheet(s) 5, H004

D92991483007 Sheet(s) 6, H007

D92991483008 Sheet(s) 7, H008

D92991492005 Sheet(s) 6, H005

D92991492006 Sheet(s) 7, H006

131
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25 Install the cable harness 5609VB.

Refer to drawing(s) :

26 Install the cable harness 5662VB.

Refer to drawing(s) :

27 Install the cable harness 5633VB.

Refer to drawing(s) :

28 Install the cable harness 5664VB.

Refer to drawing(s) :

29 Install the cable harness 5670VB.

Refer to drawing(s) :

30 Install the cable harness 5675VB.

Refer to drawing(s) :

31 Install the cable harness 5660VB.

Refer to drawing(s) :

D92991494003 Sheet(s) 4, H003

D92991494004 Sheet(s) 3, H004

D92997043001 Sheet(s) 1 - 4

D92997043002 Sheet(s) 5 and 6

D92997043003 Sheet(s) 7 and 8

D92997043004 Sheet(s) 9 - 11

D92997043005 Sheet(s) 12 and 13

D92997043006 Sheet(s) 14 and 15

D92997043007 Sheet(s) 16 - 23

132
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REVISION No. : 01 — Apr 27/07 Page :

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Refer to drawing(s) :

(bn) Do the modification to the routing of the hydra

between FR46 and FR51.

Refer to Kit 281145D82R01

Refer to drawing(s) :

NOTE : This drawing contains the consumable mate

— External Top Coat (Polyurethane) (Mat N

(bo) Do the levelling of the cargo roller tracks.

Refer to drawing(s) :

C. TEST

(1) Config. 01

(a) Job Set-up

1 Install the cover 148AZ, (Refer to AMM 57-17

401).

2 Install the Green hydraulic reservoir, (Refe

29-11-41 Page block 401).

3 If necessary, install the MLG torque tube as

to AMM 32-33-17 Page block 401).

4 On each connector that you disconnected, do a 

to make sure that :

(Refer to ESPM 20-52-10)

— The label of the plug is the same as the la

receptacle

D92991420005 Sheet(s) 6, H005

D92991420006 Sheet(s) 5, H006

D93070516000 Sheet(s) 1 - 6

D25573525006 Sheet(s) 13 - 16

133
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c Make sure that the electrical connectors a

in a correct condition.

d Connect the connectors to the battery.

e Turn the knurled nut a quarter turn.

6 Remove all the warning notices.

7 Energize the aircraft electrical circuits, (

24-41-00 Page block 201).

(b) Preliminary tests

NOTE : If the aircraft is operated in CAT3 condi

must also do the LAND CAT3 capability te

AMM 22-97-00 Page block 501).

1 Do the operational test of the instrument and 

integral lighting, (Refer to AMM 33-13-00 Pag

2 Do the operational test of the annunciator l

system in the cockpit, (Refer to AMM 33-14-00 

501).

3 Do the operational test of the avionics equi

ventilation system, (Refer to AMM 21-26-00 Pa

4 Do the operational test of the AFS, (Refer to 

Page block 501).

5 Do the operational test of the EIS, (Refer to 

Page block 501).

6 Do the operational test of the ECAM control 

to AMM 31-50-00 Page block 501).

7 Do the ground scanning of the central warning 

(Refer to AMM 31-50-00 Page block 501).

(c) Tests

1 Tests after the removal/installation of the 

equipment

134
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Data Acquisition Concentrator (SDAC) (1WV

(Refer to AMM 31-55-34 Page block 401).

d Do the test after the removal/installatio

and Flap Control Computer (SFCC) (21CV, 22

to AMM 27-51-34 Page block 401).

e Do the BITE test of the FLSCU, (Refer to A

Page block 501).

2 Test after the disconnection/connection of t

13VC, 43VC, 112VC, 1990VC and 2206VC

a Do the BITE test of the landing gear, (Ref

32-69-00 Page block 501).

3 Test after the disconnection/connection of t

1918VC, 1972VC, 1973VC, 2450VC and 2451VC

a Do the functional (BITE) test, (Refer to A

Page block 501).

4 Test after the disconnection/connection of t

1970VC and 1916VC

a Do the status report (BITE), (Refer to AMM 

block 501).

5 Test after the disconnection/connection of t

2200VC

a Do the BITE test of the BSCU, (Refer to AM

Page block 501).

6 Test after the disconnection/connection of t

288VC

a Do the operational test of the Elevator a

Computers (ELACs), (Refer to AMM 27-93-00 

501).

7 Test after the disconnection/connection of t

2453VC

a Included in the preliminary tests.

135
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a Do the operational test of the lavatory sm

system, (Refer to AMM 26-17-00 Page block 

10 Test after the disconnection/connection of t

240VC, 281VC, 283VC and 1152VC

a Do the operational test of the engine fire 

detection (loop/squib), (Refer to AMM 26-

block 501).

11 Tests after the disconnection/connection of t

1945VC

a Do the operational test of the cockpit and 

temperature control with CFDS/MCDU, (Refe

21-63-00 Page block 501).

b Do the BITE test of the landing gear, (Ref

32-69-00 Page block 501).

12 Test after the disconnection/connection of t

1266VC and 2216VC

a Do the operational test of the wing-tank f

(Refer to AMM 28-21-00 Page block 501).

13 Test after the disconnection/connection of t

1270VC

a Make sure that circuit breaker 1KT is clo

voltage check at pin C of terminal block 

connector 2, to make sure that there is 1

14 Test after the disconnection/connection of t

1947VC

a Do the operational test of the flow contro

indicating system, (Refer to AMM 21-51-00 

501).

15 Test after the disconnection/connection of t

202VC, 206VC, 208VC, 210VC, 212VC, 214VC, 21

217VC, 218VC, 219VC, 220VC, 222VC, 224VC, 22

227VC, 228VC, 229VC, 230VC, 231VC, 232VC, 234

236VC, 237VC, 239VC, 276VC, 278VC, 280VC, 282

290VC, 292VC, 294VC and 296VC.

136
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17 Tests after the disconnection/connection of t

221VC

a Do the operational test of the APU fire a

detection system, (Refer to AMM 26-13-00 

501).

18 Test after the disconnection/connection of t

223VC

a Do the operational test of the Enhanced GP

test function, (Refer to AMM 34-48-00 Page 

19 Tests after the removal/installation of the S

93VU and 94VU

a Do the test after the removal/installatio

Quantity Indicating Computer (FQIC) (3QT), 

28-42-34 Page block 401).

b Do the test after the removal/installatio

and Flap Control Computer (SFCC) (21CV, 22

AMM 27-51-34 Page block 401).

c Do the test after the removal/installatio

Fuel-Level Sensing Control-Unit (FLSCU) (

(Refer to AMM 28-46-34 Page block 401).

d Do the test after the removal/installatio

Brake/Steering Control Unit (BSCU) (10GG), 

32-42-34 Page block 401).

e Do the test after the removal/installation 

Auxiliary Power Control Unit (GAPCU) (24XG

AMM 24-41-34 Page block 401).

f Do the test after the removal/installatio

Landing gear Control and Interface Unit (

(Refer to AMM 32-31-71 Page block 401).

g Do the test after the removal/installatio

Smoke-Detection Control Unit (SDCU) (10WQ)

AMM 26-17-34 Page block 401).

h Do the test after the removal/installatio

cargo heat controller (10HC), (Refer to AM

Page block 401).

137
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

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20 Do a voltage check at pin 2 of each circuit 

follows, in the Rear C/B Panel 121VU, to make 

there is 28VDC voltage :

2EN1, 2WZ, 48WV, 14WV, 1EN1, 4EN1, 5CC2, 15CC

4QP, 1QE, 3QG, 4QG, 2QT, 3GS, 2RC2, 8CV, 20C

21CE3, 19CE3, 2GG and 183GQ.

21 Do a voltage check at pin 2 of each circuit 

follows, in the Rear C/B Panel 121VU, to make 

there is 115VDC voltage :

30QA, 11WT2, 12WT2, 3JH2, 10WT2, 2WW and 2WV

(d) Do the test of the ACT switching panel 2028VU.

1 Make sure that the electrical circuits are en

to AMM 24-41-00 Page block 201).

2 Remove the safety clip(s) and tag(s) and clos

circuit breaker(s) :

3 Set the power switch 5MY to ON.

4 Make sure that on the switching panel 2028VU 

are in ON position.

5 Operate the CLS.

a All PDUs must run in the commanded directi

6 On the switching panel 2028VU, set the switc

to OFF.

7 Operate the CLS.

a The PDU 108MY, position 31 (below ACT1) mu

All the other PDUs must run in the command

8 On the switching panel 2028VU, set the switc

to OFF.

PANEL DESIGNATION FIN LOCA

2001VU SEMI AUTO CLS-AFT 102MY D06

2001VU SEMI AUTO CLS-AFT 103MY D08

138
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11 Set the power switch 5MY to OFF.

12 Set the aircraft in normal operating positio

(e) Do an operational test of the CLS (Refer to AMM 

block 501).

(f) Do an operational test of the fuel quantity ind

(Refer to AMM 28-42-00 Page block 501).

(g) Do a status report (BITE) of the fuel quantity 

system (Refer to AMM 28-42-00 Page block 501).

(h) Do a leak test of the ACT shroud system and the 

refer to Appendix 01 .

(i) Do the tests of the cabin pressure control and m

system, refer to AMM 21-31-00 Page block 501.

(j) Do the tests of the cockpit and cabin temperatu

system, refer to AMM 21-63-00 Page block 501.

(k) Do the tests after the removal/installation of t

1CC2), refer to AMM 22-66-34 Page block 401.

(l) Do the operational test of the VHF system, refe

23-12-00 Page block 501.

(m) Do the tests of the service interphone system, 

23-44-00 Page block 501.

(n) Do the tests of the cockpit voice recorder, refe

23-71-00 Page block 501.

(o) Do the tests after the removal/installation of t

transformer(42XS), refer to AMM 24-23-17 Page b

(p) Do the tests after the removal/installation of t

control unit (1XS), refer to AMM 24-23-34 Page 

(q) Do the tests after the removal/installation of t

generator(8XS), refer to AMM 24-23-51 Page bloc

(r) Do the tests after the removal/installation of t

auxiliary generator contactor(3XS), refer to AMM 

block 401.

139
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control assembly of the offwing escape slides, 

25-62-43 Page block 401.

(v) Do the test after the removal/installation of t

escape slides reservoirs, refer to AMM 25-62-46 

401.

(w) Do the tests of the engine fire and overheat det

refer to AMM 26-12-00 Page block 501.

(x) Do the tests of the APU fire and overheat detect

refer to AMM 26-13-00 Page block 501.

(y) Do the tests of the engine fire extinguishing sy

AMM 26-21-00 Page block 501.

(z) Do the tests of the APU fire extinguishing syste

AMM 26-22-00 Page block 501.

(aa) Do the tests of the rudder hydraulic actuation, 

27-24-00 Page block 501.

(ab) Do the tests of the elevator hydraulic actuation

27-34-00 Page block 501.

(ac) Do the tests of the flaps electrical control and 

system, refer to AMM 27-51-00 Page block 501.

(ad) Do the tests of the flap system, refer to AMM 2

block 501.

(ae) Do the tests of the slat electrical control and 

system, refer to AMM 27-81-00 Page block 501.

(af) Do the tests of the slat system, refer to AMM 2

block 501.

(ag) Do the test after the removal/installation of t

position transducer unit, refer to AMM 27-92-15 

401.

(ah) Do the test after the removal/installation of t

control accelerometer, refer to AMM 27-92-16 Pag

(ai) Do the test of the side stick assembly, refer to 

Page block 501.

140
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(am) Do the test of the FCDC system, refer to AMM 27

block 501.

(an) Do the tests of the intercell transfer system, 

28-15-00 Page block 501.

(ao) Do the tests of the main fuel pump system, refe

28-21-00 Page block 501.

(ap) Do the tests of the APU fuel pump system, refer 

28-22-00 Page block 501.

(aq) Do the tests of the fuel crossfeed system, refe

28-23-00 Page block 501.

(ar) Do the tests of the engine LP fuel shut off syst

AMM 28-24-00 Page block 501.

(as) Do an operational test of the Refuel/Defuel Syst

AMM 28-25-00 Page block 501).

(at) Do the tests of the additional center tank tran

refer to AMM 28-28-00 Page block 501.

(au) Do the tests of the APU LP fuel shut off system

28-29-00 Page block 501.

(av) Do the tests of the fuel quantity indicating sy

AMM 28-42-00 Page block 501.

(aw) Do the tests of the fuel tank level sensing syst

AMM 28-46-00 Page block 501.

(ax) Do the tests of the green main hydraulic power 

to AMM 29-11-00 Page block 501.

(ay) Do the tests after the removal/installation of t

hydraulic reservoir, refer to AMM 29-11-41 Page 

(az) Do the tests of the blue main hydraulic power sy

AMM 29-12-00 Page block 501.

(ba) Do the tests of the yellow main hydraulic power 

to AMM 29-13-00 Page block 501.

141
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

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(be) Do the tests of the power transfer unit (PTU), 

29-23-00 Page block 501.

(bf) Do the tests of the yellow auxiliary hydraulic 

refer to AMM 29-24-00 Page block 501.

(bg) Do the test of the hydraulic fluid quantity indi

refer to AMM 29-31-00 Page block 501.

(bh) Do the tests of the hydraulic fluid pressure ind

system, refer to AMM 29-32-00 Page block 501.

(bi) Do the tests after the removal/installation of t

transmitters, refer to AMM 29-33-11 Page block 4

(bj) Do the tests of the hydraulic reservoir pressur

indicating system, refer to AMM 29-34-00 Page b

(bk) Do the tests of the centralized fault display i

system, refer to AMM 31-32-00 Page block 501.

(bl) Do the tests of the digital flight data recordi

refer to AMM 31-33-00 Page block 501.

(bm) Do the tests of the central warning system, refe

31-50-00 Page block 501.

(bn) Do the tests after the removal/installation of t

to AMM 31-55-34 Page block 401.

(bo) Do the tests of the normal extension/retraction 

gear, refer to AMM 32-31-00 Page block 501.

(bp) Do a functional test of the free-fall extension 

to AMM 32-33-00 Page block 501.

(bq) Do the tests of the normal braking system, refe

32-42-00 Page block 501.

(br) Do the tests of the alternate braking system wit

refer to AMM 32-43-00 Page block 501.

(bs) Do the tests of the alternate braking system wit

anti-skid, refer to AMM 32-44-00 Page block 501

142
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(bw) Do the tests of the nose wheel steering, refer t

Page block 501.

(bx) Do the tests of the service area lighting, refe

33-31-00 Page block 501.

(by) Do the tests of the wheel well lighting, refer t

Page block 501.

(bz) Do the test of the navigation lights, refer to A

Page block 501.

(ca) Do the tests of the landing lights, refer to AMM 

block 501.

(cb) Do the tests of the anti-collision/strobe light

AMM 33-48-00 Page block 501.

(cc) Do the tests of the cabin emergency lighting, re

33-51-00 Page block 501.

(cd) Do the tests of the overspeed warnings in the s

landing gear extended configuration, refer to AM

Page block 501.

(ce) Do the tests of the oxygen control and indicati

refer to AMM 35-23-00 Page block 501.

(cf) Do the tests of the engine bleed air supply syst

AMM 36-11-00 Page block 501.

(cg) Do the tests of the APU bleed air supply and cro

system, refer to AMM 36-12-00 Page block 501.

(ch) Do the tests after the removal/installation of t

electronic control box(59KD), refer to AMM 49-61

401.

(ci) Do the tests of the APU emergency shutdown circ

AMM 49-62-00 Page block 501.

(cj) Do the tests of the cargo compartment door elect

system, refer to AMM 52-35-00 Page block 501.

(ck) Do the tests of the engine interface unit, refe

73-25-34 Page block 501.

143
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(1) Config. 01

(a) Make sure that the work areas are clean and clea

other items of equipment.

(b) Install the belly fairing panels 147FB, 148FB, 

197GB, 198BB, 198GB and 198GB.

(c) In the passenger compartment, install the compon

removed for access :

— the insulation blankets, (Refer to AMM 25-80-0

201)

— the floor panels, (Refer to AMM 53-32-12 Page 

AMM 53-42-12 Page block 401)

— the textile floor covering, (Refer to AMM 25-

block 401)

— the lower sidewall (dado) panels, (Refer to AM

Page block 401)

— the upper sidewall panels, (Refer to AMM 25-23

401)

— the cove light panels, (Refer to AMM 25-23-48 

401)

— the ceiling panels, (Refer to AMM 25-23-41 Pag

— the overhead stowage compartments, (Refer to A

Page block 401)

— the passenger seats, (Refer to AMM 25-21-41 Pa

(d) In the FWD cargo compartment, install the compon

removed for access :

— the floor panels, (Refer to AMM 53-22-14 Page 

— the sidewall panels, (Refer to AMM 25-54-12 Pa

— the ceiling panels, (Refer to AMM 25-54-12 Pag

(e) In the AFT cargo compartment, install the compon

removed for access :

144
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tank 6QT (Refer to AMM 28-42-22 Page block 401)

(g) Install the outlet PN D2821302620000, (Refer to 

(h) In the forward cargo compartment, install the pa

131AW, 131BW, 131CW, 131DW, 132AW, 131HC, 131LC

and 131CC, (Refer to AMM 06-41-53 Page block 1)

(i) In the cockpit, install the lining panels 211HC, 

212KW, 212JW and 212HW, (Refer to AMM 06-41-53 

and AMM 25-13-41 Page block 401).

(j) Refuel the center tank, (Refer to AMM 28-25-00 

301).

(k) Close the avionics door 822, (Refer to AMM 52-41

201).

(l) Remove the safety equipment and close the FWD a

compartment doors, (Refer to AMM 52-30-00 Page 

(m) Remove the safety equipment and close the MLG do

AMM 32-12-00 Page block 201).

(n) Remove the access platform(s).

(o) De-energize the aircraft electrical circuits, (

24-41-00 Page block 201).

(p) Lower the aircraft, (Refer to AMM 07-11-00 Page 

(q) Restore the systems and the aircraft to normal o

condition.

E. DOCUMENTATION

Write in the applicable aircraft records that you have don

given in the Service Bulletin.

145
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

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This Page Intentionally Left Blank

146
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

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Figure 1 Sheet 1 (Goto A3 section)

Config. 01: Hook-up Chart (Kit B04)

147
6 DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page : 1 of 

Printed in FRANCE © AIRBUS, 2007 All rights reserved

(a) Obey the fuel safety procedure, refer to AMM 28

block 301.

(b) Do the EIS start procedure (Upper ECAM DU and lo

(Refer to AMM 31-60-00 Page block 201).

(c) On the ECAM control panel push the FUEL pushbutt

the lower ECAM DU the FUEL page comes into view

(d) Make certain that the indications are normal and 

installed.

(e) Remove the safety clip(s) and the tag(s) and clo

(these) circuit breaker(s) :

(f) Operational test of the annunciator light test 

1 Do an operational test of the annunciator lig

in the cockpit (Refer to AMM 33-14-00 Page b

NOTE : During the test, make sure that, on pa

40VU, the annunciator lights of the AC

push-button switch stay off.

(g) In the AFT area of the RH main landing gear bay

the elbow nut, item (1). Loosen the ACT cavity d

item (2), turn the elbow to approximately 180 de

the nut again. Make sure that the tank interspa

connection(s) have blanks installed.

(h) Connect a Ground Pressure Generator (GPG) to the 

ACT cavity drain-line.

(i) Open the ACT transfer valve.

1 Open, safety and tag this circuit breaker :

PANEL DESIGNATION FIN LOCA

122VU LIGHTING/ANN LT SPLY/XFMR/BUS 1 26LP 04 X

49VU LIGHTING/XFMR/115.5V/ESS BUS 29LP 03 H

122VU LIGHTING/ANN LT SPLY/XFMR/STAT

INV

28LP 03 X
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

circuit breakers :

and on 40VU, pushing the ACT P/B. P/B lights 

must come on.

3 In the LH MLG Bay on the rear side of the ce

check at the mechanical indicator that the AC

open.

4 Make sure that the ACT pump is not running.

(2) Leak Test of the ACT shroud system and drain lines.

(a) Test Procedure

1 On the GPG set the air supply maximum pressu

(20 psi).

2 Introduce air from the GPG into the ACT syste

Increase the pressure to 1,4 bar (20 psi) and 

this pressure for 15 minutes.

3 The system must not leak. The pressure in the 

not decrease. If a leak is found, a repair mu

the test procedure done again.

(b) Close up

1 Release the pressure from the ACT system dra

disconnect the GPG from the ACT cavity drain

2 Loosen the ACT cavity drain-line nut, item (2

elbow to approximately 180 deg. and tighten t

3 Reconnect the elbow nut, item (1) to the ACT 

drain-line.

2. Leak Test of the ACT Provisions in the Center Tank.

A. Leak Test

PANEL DESIGNATION FIN LOCA

121VU ACT XFR VALVE MAN CTL 30QH 29 N

121VU ACT XFR VALVE AUTO CTL 9QH 29 P

2
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

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Printed in FRANCE © AIRBUS, 2007 All rights reserved

(b) Connect the fuel bowser to the refuel coupling.

(2) Test Procedure

(a) Operate the leak monitors for the ACT shroud dra

interspace drain.

(b) Operate the high level switch on 800VU, check t

"high level" lamps illuminate.

(c) With all refuel valves shut, put pressure on the 

gallery via the bowser. The gallery will quickly 

fuel. Any additional flow, due to system leakage

exceed 1 litre/min.

(d) Press and hold the "Manual" button on the ACT re

The ACT refuel/transfer line will quickly prime 

additional flow, due to system leakage, should 

litre/min.

(e) Release the "Manual" button on the ACT refuel va

(f) On the panel 800VU, select the refuel valve for 

tank to "Open".

(g) On the panel 800VU, select "Refuel" on the Mode 

(h) Refuel the center tank until it is stopped by t

sensors.

(i) On the refuel panel 800VU, set all refuel valve

(j) Examine the rear spar of the center tank and the 

center tank for signs of fuel leakage. Pay part

attention to the connections for the ACT vent l

refuel/transfer line, and the equipment mounted 

manhole access door for the center tank. If a le

carry out a repair and do the test procedure aga

(k) Operate the leak monitors for the ACT shroud dra

interspace drain. If fuel comes out of the ACT 

leak-monitor then there is problem with the pipe

ACT refuel/transfer line. Carry out a repair and 

procedure again.

(3) After Test

3
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

Refer to Figure 3 Sheet 1

Refer to Figure 4 Sheet 1

NOTE : The test that follows is to check that the ACT pre

system does not leak and that the non-return valves 

operate correctly. The test is to be done one time 

aircraft fitted with provisions for ACT(s) before t

installation of the ACT.

(1) Test Preparation

(a) In the AFT cargo compartment, remove the ceiling 

151CC to get access to the test connectors T1 a

air pressurization system (Refer to AMM 25-55-1

401).

(b) Connect the Test Tool 1 to the test port T1.

(c) Connect the Test Tool 2 to the test port T2.

(d) Remove the datum pipe guard in the belly fairing 

blank.

(e) Make sure that the connection(s) to the ACT(s) 

installed.

(f) Close the air shut off valve.

(2) Test Procedure

(a) Introduce air from the GPG and raise the pressu

(20.0 psi), retain at this pressure for 10 minut

(b) Isolate the aircraft ACT pressurisation system f

(c) Check that the pressure indicated at T1 remains 

a ten minute period at 1.4 bar (20.0 psi). Make 

no leakage from the pipework between the upstrea

valve and the air shut-off valve and no reverse 

through the upstream non-return valve.

(d) Check that the pressure indicated at T2 remains 

sure there is no leakage through the air shut-of

(e) Open the air shut-off valve.

4
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

check the correct opening of the pressure reduc

the downstream non-return valve.

(i) Reduce the pressure on the GPG to zero and relea

pressure retained in the system at T1.

(j) Check that the pressure indicated at T2 remains 

psi). This will show the correct operation of t

non-return valve and no reverse leakage through 

(k) Bleed air from T2 to reduce pressure to zero.

(3) Acceptable Results

(a) The system must not leak. The pressure in the sy

decrease. If a leak is found, a repair must be m

test procedure done again.

(4) Close Up

(a) Release the pressure from the ACT pressurisatio

(b) Carefully remove the blank from the datum pipe 

belly fairing and replace the guard.

(c) Disconnect the test tool 1 from T1.

(d) Disconnect the test tool 1 from T2.

(e) Close the air shut-off valve.

(f) In the AFT cargo compartment, install the ceilin

151CC (Refer to AMM 25-55-11 Page block 401).

5
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

Figure 1 Sheet 1

Leak Test of the ACT Shroud System and Drain Lines

6
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

Figure 1 Sheet 2

Leak Test of the ACT Shroud System and Drain Lines

7
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

Figure 2 Sheet 1

Access to the Test Points T1 and T2

8
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

Figure 3 Sheet 1

ACT Test Arrangement - Test Tool 1

9
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

Figure 4 Sheet 1

ACT Arrangement - Test Tool 2

10
6 DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page : 1 of 

Printed in FRANCE © AIRBUS, 2007 All rights reserved

36350K10558 36399K6099
DATE : Feb 28/06 SERVICE BULLETIN No. : A320

REVISION No. : 01 — Apr 27/07 Page :

Printed in FRANCE © AIRBUS, 2007 All rights reserved

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please indicate required service:

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result in

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Planning Material Instruct

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SERVICE BULLETIN

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Figure 1 Sheet 1

Config. 01: Hook-up Chart (Kit B04)